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Full text of "Aerodynamic performance of axial-flow fan stage operated at nine inlet guide vane angles"

NASA Technical Paper 1510 






Aerodynamic Performance of 
Axial-Flow Fan Stage Operated 
at Nine Inlet Guide Vane Angles 



Royce D. Moore and Lonnie Reid 



SEPTEMBER 1979 



fVI/NSA 



UNIVERSITY OF ILLINOIS-URBANA 



3 0112 106725762 



NASA Technical Paper 1510 



Aerodynamic Performance of 
Axial-Flow Fan Stage Operated 
at Nine Inlet Guide Vane Angles 



Royce D. Moore and Lonnie Reid 
Lewis Research Center 
Cleveland, Ohio 



NASA 

National Aeronautics 
and Space Administration 



Scientific and Technical 
Information Branch 



1979 



Digitized by the Internet Archive 

in 2012 with funding from 

University of Illinois Urbana-Champaign 



http://archive.org/details/aerodynamicperfoOOmoor 



SUMMARY 

The overall performance of a fan stage suitable for vertical-lift aircraft is pre- 
sented for nine inlet guide vane angle settings. Data were obtained over the stable flow 
range at speeds from 60 to 120 percent of design for vane setting angles from -25° to 
42.5°. At design speed and design inlet guide vane angle, the stage had a peak effi- 
ciency of 0.892 at a pressure ratio of 1.322 and a flow of 25. 31 kilograms per second. 
The stall margin based on flow and pressure ratio at peak efficiency and stall was 
20 percent. 

Based on an operating line passing through the peak efficiency point at the design 
setting angle, the useful operating range of the stage at design speed is limited by stall 
at the positive setting angles (32.5 ) and by choke at the negative angles (-17.5 ). The 
calculated static thrust along the operating line varied from 68 to 114 percent of that ob- 
tained at the design setting angle. 



INTRODUCTION 

The research program on axial-flow fans and compressors for advanced air breath- 
ing engines being conducted at the NASA Lewis Research Center is primarily directed 
toward improving the performance and reducing the size, weight, and cost of these 
components. As a part of this program, experimental studies have been conducted on 
fan stages with variable-pitch-rotor-blades suitable for use in engines for powered-lift 
aircraft (refs. 1 to 7). The results from these investigations indicated that some of the 
various flight requirements could be achieved using engines with such fan stages. 

The Lewis Research Center is studying various engine concepts for vertical-lift 
aircraft. Not only are the cruise requirements more demanding than those for powered- 
lift aircraft, there is also a takeoff and landing requirement that the thrust for each en- 
gine be varied to provide aircraft stability control. Two of the methods being consid- 
ered for varying the thrust are the use of variable-pitch rotor blades and the use of var- 
iable inlet guide vanes. The performance of a fan stage with variable-pitch rotor blades 
operating over a range of angle settings is presented in reference 8. The performance 
of the same fan stage with the rotor blades at a fixed setting angle is presented in the 
report for nine inlet guide vane angles. 

The variable inlet guide vanes were designed and fabricated by Hamilton Standard 
Division of the United Technologies Corporation to be added to the 1. 38-pressure-ratio 
variable-pitch- rotor fan stage previously tested. The stage with the inlet guide vanes 



was tested by Lewis at speeds from 60 to 120 percent of design and inlet guide vane 
angles from -25 to 42.5 . It was anticipated that this angle variation would give a sig- 
nificant range in fan thrust at design speed. This report presents the overall perform- 
ance of the stage operated at nine inlet guide vane setting angles. 



TEST STAGE 

The test stage (figs. 1 and 2), designated stage 57M2, was designed and fabricated by 
the Hamilton Standard Division of the United Technologies Corporation. The rotor and 
stator are those described in reference 8. The inlet guide vanes (IGV's) were designed 
to be added to that stage. From the previous tests on the fan stage (ref. 8), it appears 
that the efficiency would be optimum at a rotor setting angle of 6° (closed) . Thus the 
rotor-blade setting angle for stage 57M2 was set at 6°. The casing diameter above the 
rotor tip was constant, and the rotor was machined to have a constant clearance from 
blade leading to trailing edge. The 20 inlet guide vanes were of NACA 63-009 series 
profiles. In their design position the vanes are alined to the axial direction. As shown 
in figure 3, the front portion of the blades was stationary, and the rear portion was 
movable. 

The stage was tested with the inlet guide vanes set at nine angles. Listed below 
are the stage designations for each setting angle: 



Stage 


Inlet guide vane 




setting angle, 




deg from design 


57M2A 





57M2B 


-10.0 


57M2C 


-17.5 


57M2D 


-25.0 


57M2E 


10.0 


57M2F 


17.5 


57M2G 


25.0 


57M2H 


32.5 


57M2I 


42.5 



APPARATUS AND PROCEDURE 

Test Facility 

The fan stage was tested in the Lewis single-stage compressor test facility, which 
is diagramed in figure 4. Atmospheric air enters the test facility at a inlet located on 
the roof of the building, and flows through the flow measuring orifice into the plenum 
chamber upstream of the test stage. The air then passes through the experimental fan 
stage into the collector and is exhausted to the facility exhaust system. 

Instrumentation 

The fan flow was determined from the measurements on a calibrated thin-plate ori- 
fice that was 38.9 centimeters in diameter. The orifice temperature was determined 
from an average of two Chromel-Constantan thermocouples. Orifice pressures were 
measured by calibrated transducers. 

Radial surveys of the flow were made upstream of the IGV's, between the IGV's 
and the rotor, between the rotor and the stator, and downstream of the stator (see fig. 1 
for axial locations). Photographs of the survey instrumentation are shown in figure 5. 
At stations and 2 total pressure, total temperature, and flow angle were measured 
with the combination probe (fig. 5(a)), and the static pressure was measured with an 18° 
wedge probe (fig. 5(b)). At stations 1 and 3 total pressure and total temperature were 
measured with the nine-element radial rake (figs. 5(c) and (d)) . The static pressure 
and flow angle were determined from the wedge probe. Each probe was positioned with 
a null-balancing stream-direction-sensitive control system that automatically alined 
the probe to the direction of flow. At station 3 the rakes were set straight ahead. At 
station 1 the rakes were set to match the IGV angle. The thermocouples were Chromel- 
Constantan for both the combination probe and the rake. 

Inner- and outer-wall static-pressure taps were located at approximately the same 
axial stations as the survey instrumentation. The circumferential locations of the sur- 
vey instrumentation along with the inner- and outer-wall static-pressure taps are shown 
in figure 6. 

An electronic speed counter, in conjunction with a magnetic pickup, was used to 
measure rotative speed (rpm). 

The estimated errors of the data based on inherent accuracies of the instrumenta- 
tion and recording system are as follows: 

Airflow, kg/sec ±0.3 

Rotative speed, rpm ±30 

Flow angle, deg ±1.0 

3 



Temperature, K ±0.6 

o 

Rotor-inlet total pressure, N/cm ±0.04 

o 

Rotor-outlet total pressure, N/cm ±0.10 

2 

Stator-outlet total pressure, N/cm ±0.10 

2 

Rotor-inlet static pressure, N/cm ±0.04 

2 

Rotor-outlet static pressure, N/cm ±0.10 

2 

Stator-outlet static pressure, N/cm ±0.10 

2 

IGV inlet total pressure, N/cm ±0.01 

2 
IGV inlet static pressure, N/cm ±0.04 



Test Procedure 

The stage survey data for each configuration were taken over a range of speeds 
from 60 to 120 percent of design speed and a range of flows from maximum to near- 
stall conditions. The data were recorded at nine radial positions for each speed and 
weight flow. 

The combination probes at stations and 2 and the wedge probes at all stations 
were traversed radially at the same time the nine-element rakes at stations 1 and 3 
were traversed circumferentially. The wedge probes were set at midgap because 
previous studies showed that the static pressure across the stator gap was constant. 
The probes and rakes were set at their initial position and values of pressure, temper- 
ature, and flow angle were recorded. The instruments are then traversed to their 
next scheduled position, and data were again recorded. When the rakes are at their 
last circumferential position, the probes are at their last radial position. 



Calculation Procedure 

Measured values of total pressure, static pressure, and total temperature were 
corrected for Mach number and streamline slope. These corrections were based on an 
average calibration for the type of instrument used. Orifice airflow, rotative speed, 
static and total pressures, and total temperatures were all corrected to standard-day 
conditions based on the IGV inlet condition. 

For the data reduction program the circumferential distributions of static pressure 
and flow angle downstream of the inlet guide vane (station 1) and stator (station 3) were 
assumed to be constant for each radial position and equal to the measured midgap val- 
ues. The nine values of total temperature were mass-averaged to obtain the stator- 
outlet temperature. The nine values of total pressure were converted to their enthalpy 
equivalents and then mass averaged. 



To obtain the overall performance, the radial values of total temperature were 
mass averaged, and the values of total pressure were converted to their enthalpy equiv- 
alent and then mass averaged as before. 

The sea-level static thrust is composed of both the momentum thrust and the pres- 
sure thrust. The momentum thrust is a product of the flow rate and the outlet velocity. 
The pressure thrust consists of a product of the outlet area and the difference between 
outlet static pressure and inlet total pressure. The symbols and equations are defined 
in appendixes A and B. 

The weight flow at stall was obtained in the following manner: during operation at 
the near-stall condition, the collector valve was slowly closed in small increments. At 
each increment the air flow was obtained. The air flow obtained just before stall oc- 
curred is defined as the stall air flow. The pressure ratio at stall was obtained by ex- 
trapolating the total pressure obtained from the survey data to the stall air flow. 



RESULTS AND DISCUSSION 

The results from this investigation are presented in three sections. The overall 
performance of the rotor and stage for the design inlet guide vane angle are presented 
first. (The rotor is the same as that presented in ref. 8, but the blades are set at 6° 
closed.) The effects of vane angle on the overall performance are then presented. 
Finally, the effects of vane angle on calculated static thrust are discussed. The overall 
performances for all nine inlet guide vane angles are presented in tables I to K. 



Performance with IGV at Design Angle 

The overall performance for the rotor and stage are presented in figures 7 and 8, 
respectively. Pressure ratio and adiabatic efficiency are presented at several flows 
for speeds of 60, 70, 80, 90, 100, 110, and 120 percent of design. The stall line is 
also shown for the overall stage performance (fig. 8). 

At design speed the rotor had a peak efficiency of 0.905. It occurred at a flow of 
24.06 kilograms per second and a pressure ratio of 1. 361. The stage peak efficiency 
of 0.892 occurred at a pressure ratio of 1. 322 and a flow of 25. 31 kilograms per sec- 
ond. The stall margin was 20 percent based on flow and pressure ratio at stall and 
peak efficiency. 



Performance Over Range of IGV Setting Angles 

Performance curves for the inlet guide vanes set at nine vane setting angles for the 
100 and 120 percent of design speeds are shown in figure 9. The stall lines are shown 
in each figure. The operating line, which passes through the design-speed peak- 
efficiency point at the 0° vane angle, was obtained by setting a constant throttle valve 
position and varying the IGV setting angle during tests. 

At both the 100 and 120 percent of design speeds, the pressure ratio and flow in- 
crease as the inlet guide vane setting angle is changed from 42.5° to -17.5°. However, 
a change in the flow characteristics is apparent as the setting angle is further changed 
to -25°. At design speed the flow -pressure ratio curve for -25° is essentially the same 
as that for -17.5° except near the stall line. The data presented were corrected to 
standard-day conditions at the IGV inlet. Had the data been corrected to rotor-inlet 
conditions, the flow-pressure ratio curve for -25° would not have been the same as that 
for -17.5°. At a setting angle of -25° the pressure losses across the IGV are consider- 
ably greater than those at -17.5°. For equivalent IGV inlet flows, the rotor will be op- 
erating at a higher corrected airflow at an angle of -25° than at -17.5°. 

At 120 percent design speed the flow-pressure ratio curve for -25° has dropped 
and is between those at the 0° and -10° angles. Preliminary survey data at 120 percent 
design speed (not presented in this report) indicate that the rotor tip element is choked 
even at a setting angle of 0°. Turning the inlet guide vanes to more negative angles 
caused this choked region to move further down the rotor blades. 

There is a considerable variation in peak efficiency over the range of vane setting 
angles. At 42.5° the design speed peak efficiency is 0.676. It continues to increase to 
a maximum of 0.892 at 0° and then decreases to 0.795 at -25°. There is a similar 
change in peak efficiency at 120 percent of design speed; however, the maximum value 
occurs at an angle of 10 . 

Based on the operating line presented, the useful range of inlet-guide-vane setting 
angle is limited: At the high negative angles, the stage choked; at the high positive 
angles, the stage stalled. 



Calculated Thrust 

The primary purpose of the variable inlet guide vane in this fan stage is to provide 
thrust modulation capability at constant blade speed. The effect of vane-angle variation 
on the calculated static thrust is presented in figure 10. Maximum calculated static 
thrust and operating line static thrust are presented for both the 100 and 120 percent of 
design speeds. 



At 100 percent of design speed (fig. 10(a)) the operating-line static thrust is nearly 
equal to maximum values except at the higher negative vane setting angles. At 120 per- 
cent of design speed the differences are more significant over the setting angle range. 
At design speed the operating line calculated static thrust varied from 3900 to 6500 new- 
tons, which corresponds to 68 to 114 percent of that obtained at as the inlet guide 
vane angle was changed from 32.5° to -17.5°. The lower limit was due to the operating 
line crossing the stall line and the upper limit was set by choking. In the application of 
this stage in an engine, a variable area exit nozzle would probably be required to 
achieve a wider range of thrust. At the more negative angles, more thrust could be 
realized by reducing the area (and flow); while at the more positive angles, increasing 
the area would move the operating line away from stall and would allow for further re- 
ductions in thrust. 



SUMMARY OF RESULTS 

The overall performance of a fan stage suitable for vertical-lift aircraft and incor- 
porating variable inlet guide vanes was determined for nine vane setting angles. Data 
were obtained over the stable flow range at rotative speeds from 60 to 120 percent of 
design. The vane angle was varied from 42. 5° to -25°. The following were the prin- 
cipal results of the investigation: 

1. At the design speed and the design inlet guide vane angle, the stage had a peak 
efficiency of 0.892 at a pressure ratio of 1.322 and a flow of 25. 31 kilograms per sec- 
ond. The stall margin based on peak efficiency and stall was 20 percent. 

2. Based on an operating line passing through the peak efficient point at the design 
vane setting angle, the useful operating range of the stage at design speed is limited by 
stall at the high positive setting angles (32.5°) and by choke at high negative setting 
angles (-17.5°). 

3. At design speed the calculated static thrust along an operating line varied from 
68 to 114 percent of that obtained at a vane angle of 0° as the inlet guide vanes were 
changed from 32.5° to -17.5°. 

Lewis Research Center, 

National Aeronautics and Space Administration, 
Cleveland, Ohio, May 9, 1979, 
505-04. 



APPENDIX A 
SYMBOLS 



A 



2 
area, m 



2 
A annulus area at inlet guide vane leading edge, m 

2 
A f frontal area at inlet guide vane leading edge, m 

C specific heat at constant pressure, 1004 J /kg K 

N rotative speed, rpm 

2 
P total pressure, N/cm 

2 
p static pressure, N/cm 

SM stall margin 

T total temperature, K 

U wheel speed, m/sec 

V air speed, m/sec 

W airflow, kg/sec 

y ratio of specific heats 

5 ratio of inlet guide vane inlet total pressure to standard pressure of 

10.13 N/cm 2 

r\ efficiency 

6 ratio of inlet guide vane inlet total temperature to standard temperature 

at 288.2 K 

p density, kg /sec 

Subscripts: 

ad adiabatic 

LE blade leading edge 

mom momentum-rise 

TE blade trailing edge 

z axial direction 

6 tangential direction 



Definitions and Units Used in Tables: 

2 
AREA area, m 

AIRFLOW equivalent airflow, kg/sec 

ROTATIVE SPEED rotative speed, rpm 



APPENDIX B 
EQUATIONS 
Adiabatic (temperature rise) efficiency - 

v(r-D/r 

TE 

, P LE 
"ad 






T TE j 

t le" 



Momentum- rise efficiency 





/ P \(7-i)/y 


"mom 


( uv e ) TE - ( uv 9 ) LE 




T LE C p 



Equivalent airflow 



Equivalent rotative speed 



Airflow per unit annulus area 



wVe 



_N_ 



wVe \ 
a„_ 



10 



Airflow per unit frontal area 



A f 



(B6) 



Head -rise coefficient 



C p T LE 



U Up 



\(y-D/y 

*TE 



LE 



(B7) 



Flow coefficient 



Static thrust - 



U tip/LE 



(B8) 



Stall margin 



SM 



\ P LE /stall v \j /ref 



W 



TE 



P LE/ref V 6 /sta11 



V£ 



- 1 



xlOO 



(B9) 



pV z A TE + (p TE - P LE )A TE 



(BIO) 



11 



REFERENCES 

1. Kovich, George; and Steinke, Ronald J.: Performance of a Low-Pressure-Ratio 

Low- Tip Speed Fan Stage with Blade Tip Solidity of 0.65. NASA TM X-3341, 1976. 

2. Kovich, George; Tysl, Edward R.; and Moore, Royce D.: Performance of a Low- 

Pressure Ratio Fan Stage at Two Off- Design Blade Setting Angles. NASA TM 
X-3447, 1977. 

3. Lewis, George W., Jr.; Moore, Royce D.; and Kovich, George: Performance of a 

1.20 Pressure- Ratio STOL Fan Stage at Three Rotor Blade Setting Angles. NASA 
TM X-2837, 1973. 

4. Lewis, George W. , Jr.; and Tysl, Edward R.: Overall and Blade-Element Per- 

formance of a 1.20-Pressure-Ratio Fan Stage at Design Blade Setting Angle. NASA 
TM X-3101, 1974. 

5. Lewis, George W. , Jr.; Osborn, Walter M.; and Moore, Royce D. : Overall and 

Blade- Element Performance of a 1. 20-Pressure Ratio Fan Stage with Rotor Blades 
Reset Minus 5°. NASA TM X-3338, 1976. 

6. Lewis, George W. , Jr.; and Kovich, George: Overall and Blade-Element Perform- 

ance of a 1. 20-Pressure Ratio Fan Stage with Rotor Blades Reset Minus 7°. NASA 
TM X-3342, 1976. 

7. Moore, Royce D. ; and Kovich, George: Aerodynamic Performance of Two Variable- 

Pitch Fan Stages. NASA TM X-73416, 1976. 

8. Moore, Royce D. ; and Osborn, Walter M.: Aerodynamic Performance of a 1.38- 

Pres sure- Ratio Variable- Pitch Fan Stage. NASA TP-1502, 1979. 



12 



TABLE I. - OVERALL PERFORMANCE OF STAGE 57M2A 



(a) 120 Percent of design speed 



READING NUMBER 
16V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
ICV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0461 


0460 


0459 


0458 


0457 


0.999 


0.999 


0.999 


0.999 


0.999 


1.587 


1.529 


1.457 


1.367 


1.310 


0.981 


0.995 


0.991 


0.980 


0.967 


1.000 


1.000 


0.999 


0.999 


0.999 


1.166 


1.156 


1.143 


1.125 


1.116 


0.99S 


0.99S 


0.995 


0.996 


0.995 


0.849 


0.826 


0.796 


0.746 


0.688 


0.894 


0.876 


0.832 


0.765 


0.718 


0.394 


0.354 


0.308 


0.250 


0.213 


0.371 


0.395 


0.407 


0.409 


0.410 


133.33 


140.60 


144.42 


145.07 


145.23 


145.67 


1S3.61 


157.79 


158.50 


158.67 


27.02 


28.50 


29.27 


29.40 


29.44 


27.00 


28.55 


29.23 


29.38 


29.39 


27.11 


28.66 


29.31 


29.41 


29.45 


25.86 


27.54 


28.58 


28.83 


29.06 


27.27 


28.76 


29.23 


28.86 


29.09 


13079.7 


13141.7 


13133.1 


13122.0 


13097.1 


120.2 


120.7 


120.6 


120.5 


120.3 


1.555 


1.520 


1.442 


1.338 


1.265 


1.160 


1.149 


1.136 


1.121 


1.110 


0.842 


0.851 


0.811 


0.718 


0.634 



(b) 110 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0456 


0454 


0453 


0451 


0450 


0.999 


0.999 


0.999 


0.999 


0.999 


1.489 


1.453 


1.412 


1.323 


1.266 


0.980 


0.989 


0.990 


0.984 


0.970 


1.000 


1.000 


1.000 


1.000 


1.000 


1.138 


1.130 


1.123 


1.105 


1.097 


0.996 


0.993 


0.995 


0.997 


0.995 


0.876 


0.863 


0.844 


0.791 


0.720 


0.920 


0.931 


0.902 


0.811 


0.752 


0.390 


0.364 


0.332 


0.263 


0.219 


0.362 


0.399 


0.416 


0.427 


0.429 


120.99 


131.09 


136.19 


139.69 


139.84 


132.19 


143.23 


148.80 


152.62 


152.79 


24.52 


26.57 


27.60 


28.31 


28.34 


24.49 


26.58 


27.61 


28.22 


28.27 


24.55 


26.63 


27.62 


28.28 


28.33 


23.74 


25.81 


26.92 


2^.63 


27.97 


24.44 


26.34 


27.24 


27.56 


27.71 


11987.7 


11962.0 


11973.7 


11968.9 


11956.4 


110.1 


109.9 


110.0 


109.9 


109.8 


1.458 


1.435 


1.396 


1 .300 


1.227 


1.133 


1.123 


1.117 


1.102 


1.091 


0.858 


0.885 


0.857 


0.765 


0.662 


3 Percent of design speed 








0449 


0448 


0447 


0446 


0445 


0.999 


0.999 


0.999 


0.999 


0.999 


1.380 


1.361 


1.338 


1.302 


1.226 


0.986 


0.989 


0.989 


0.982 


0.972 


1.000 


1.000 


0.999 


0.999 


1.000 


1.111 


1.104 


1.098 


1.090 


1.079 


0.996 


0.996 


0.996 


0.996 


0.996 


0.869 


0.885 


0.883 


0.874 


0.761 


0.920 


0.945 


0.940 


0.905 


0.791 


0.371 


0.353 


0.330 


0.295 


5.223 


0.358 


0.392 


0.415 


0.445 


0.453 


109.70 


118.65 


124.87 


132.90 


13S.60 


119.85 


129.63 


136.44 


145.20 


148.15 


22.23 


24.05 


25.31 


26.94 


27.43 


22.24 


24.06 


25.32 


26.94 


?7.40 


22.22 


24.06 


25.35 


26.95 


27.43 


21.52 


23.52 


24.83 


26.50 


26.84 


21.96 


23.62 


24.74 


26.16 


26.67 


10868.6 


10858.5 


10863.8 


10876.6 


10893.9 


99.8 


99.7 


99.8 


99.9 


100.1 


1.359 


1.344 


1.322 


1.277 


1.191 


1.106 


1 .099 


1.093 


1.085 


1 .074 


0.862 


0.891 


0.892 


0.851 


0.693 



13 



Continued. OVKRALL PKIU-TJKM ANCK OF STAGE 57M2A 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
ICV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



(d) 90 Percent of design speed 








utt 


046S 


0464 


0463 


0462 


0.99? 


0.999 


0.999 


0.999 


0.999 


1.295 


1.278 


1 .256 


1.235 


1.189 


0.989 


0.992 


0.992 


0.988 


0.976 


1 .000 


0.999 


0.999 


0.999 


0.999 


1.089 


1.082 


1 .075 


1.069 


1.063 


0.997 


0.998 


0.998 


0.998 


0.997 


0.865 


0.888 


0.899 


0.898 


0.810 


0.924 


0.945 


0.952 


0.939 


0.854 


0.360 


0.339 


0.312 


0.286 


0.232 


0.347 


0.383 


0.417 


0.446 


0.478 


96.44 


105.44 


114.03 


121 .13 


128.83 


105.37 


115.20 


124.58 


132.34 


140.75 


19.55 


21.37 


23.11 


24.55 


26.11 


19. S7 


21.36 


23.11 


24. S3 


26.03 


19.54 


21.36 


23.12 


24.53 


26.07 


19.03 


20.82 


22.67 


24.09 


25.48 


19.38 


21.01 


22.61 


23.90 


2S.3S 


9749.3 


9735.7 


9740.1 


9747.6 


9736.0 


89.6 


89.4 


89. S 


89.5 


89.4 


1.280 


1.268 


1.245 


1.218 


1.159 


1.085 


1 .079 


1.072 


1.066 


1.058 


0.859 


0.893 


0.900 


0.876 


0.742 



(e) 80 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0471 


0470 


0469 


0468 


0467 


1.000 


0.999 


0.999 


0.999 


0.999 


1.228 


1.214 


1.194 


1.177 


1.153 


0.992 


0.992 


0.990 


0.984 


0.976 


1.000 


1.000 


1.000 


0.999 


0.999 


1.070 


1.063 


1.057 


1.053 


1.048 


0.998 


0.998 


0.998 


0.997 


0.997 


0.869 


0.900 


0.907 


0.903 


0.859 


0.930 


0.963 


0.963 


0.954 


0.910 


0.349 


0.327 


0.297 


0.272 


0.236 


0.345 


0.388 


0.425 


0.4S8 


0.490 


86.30 


96.28 


104.71 


111.95 


119.04 


94.29 


105.19 


114.40 


122.31 


130.05 


17.49 


19.52 


21.22 


22.69 


24.13 


17.47 


19.51 


21.22 


22.67 


24.08 


17.46 


19.49 


21.19 


22.66 


24.08 


16.92 


19.12 


20.87 


22.39 


23.67 


17.19 


18.97 


20.54 


21.83 


23.23 


8701.3 


8707.3 


8706.8 


8689.7 


8691.4 


79.9 


80.0 


80.0 


79.8 


79.8 


1.217 


1.204 


1.182 


1.157 


1.124 


1.067 


1.061 


1.055 


1 .049 


1 .044 


0.866 


0.893 


0.893 


0.862 


0.766 


Percent of design speed 








0477 


0476 


0475 


0474 


0473 


1.000 


1.000 


0.999 


0.999 


0.999 


1.169 


1.1S9 


1.143 


1.129 


1.111 


0.994 


0.995 


0.991 


0.987 


0.981 


1.000 


1.000 


1. 000 


1.000 


0.999 


1.052 


1.048 


1.043 


1.039 


1.036 


0.998 


0.999 


0.998 


0.998 


0.998 


0.875 


0.901 


0.916 


0.901 


0.858 


0.941 


0.970 


0.979 


0.963 


0.927 


0.339 


0.318 


0.287 


0.259 


0.224 


0.343 


0.383 


0.429 


0.464 


0.500 


75.35 


83.83 


93.17 


100.18 


107.60 


82.33 


91.59 


101.79 


109.46 


117.56 


15.27 


16.99 


18.88 


20.31 


21 .81 


15.31 


16.99 


18.91 


20.29 


21.79 


15.28 


16.98 


18.88 


20.28 


21.77 


14.82 


16.61 


18.66 


19.96 


21.28 


15.00 


16.52 


18.28 


19. S2 


21 .00 


7611.1 


7608.9 


7603.2 


7600.8 


7607.8 


69.9 


69.9 


69.8 


69.8 


69.9 


1.161 


1.152 


1.132 


1.113 


1.090 


1.050 


1.046 


1 .040 


1.037 


1 .033 


0.866 


0.895 


0.892 


0.850 


0.748 



14 



Concluded. OVERALL PERFORMANCE OF STAGE 57M2A 
(g) 60 Percent of design speed 



READING NUMBER 
I6V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
I6V TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT I6V INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0481 


0480 


0479 


0478 


1.000 


1.000 


0.999 


0.999 


1.122 


1.109 


1.095 


1.078 


0.995 


0.995 


0.991 


0.984 


1.000 


1.000 


1.000 


1.000 


1.038 


1.033 


1.129 


1.025 


0.999 


0.999 


0.999 


0.999 


0.877 


0.914 


0.915 


0.867 


0.948 


1.000 


0.993 


0.955 


0.332 


0.298 


0.2S9 


0.213 


0.336 


0.404 


0.457 


0.513 


63.68 


76.15 


85.79 


95.35 


69.57 


83.20 


93.73 


104.17 


12.91 


15.43 


17.39 


19.33 


12.94 


15.46 


17.40 


19.31 


12.91 


15.42 


17.37 


19.27 


12.50 


15.23 


17.11 


18.84 


12.67 


14.96 


16.73 


18.59 


6534.2 


6522.9 


6534.0 


6514.1 


60.0 


59.9 


60.0 


59.8 


1.116 


1 .103 


1.084 


1.060 


1.037 


1 .031 


1.027 


1.023 


0.860 


0.902 


0.859 


0.714 



15 



TABLE II. - OVERALL PERFORMANCE OF STAGE 57M2H 



(a) 120 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOH PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0506 
0.998 
1 .582 
0.990 
1.000 
1.173 
0.996 
0.811 
0.837 
0.394 
0.396 
140.12 
153.09 
28.40 
28.45 
28.68 
27.85 
28.96 
13057.6 
119.9 



.S63 

.168 



0502 
0.998 
1 .572 
0.991 
1.000 
I .170 
0.996 
0.810 
0.838 
0.387 
0.404 
142.54 
155.73 
28.89 
28.91 
29.16 
28.43 
29.38 
13068.8 
120.1 



1.555 
1 .165 

0.813 



C503 
0.998 
1.557 
0.987 
0.999 
1.167 
0.996 
0.807 
0.840 
0.377 
0.416 
146.45 
160.00 
29.68 
29.66 
29.89 
29.55 
29.80 
13077.2 
120.1 



1.533 
1.162 
0.802 



0501 
0.998 
1.489 
0.981 
0.999 
1 .156 
0.996 



. 


773 


0. 


796 


0. 


332 


0. 


421 


143 


.33 


\62 


.06 


30 


.06 


29 


.96 


30 


.17 


29 


.89 


29 


.47 


308 


:.a 


120.2 


1. 


458 


1. 


ISO 


0. 


757 



0500 
0.998 
1.419 
0.970 
0.999 
1.144 
0.995 
0.731 
0.748 
0.288 
0.423 
148.66 
162.42 
30.13 
30.04 
30.25 
30.07 
29.17 
13061.5 
120.0 



1.374 
1.138 
0.690 



049) 
0.998 
1.350 
0.943 
0.999 
1.134 
0.993 
0.667 
0.703 
0.243 
0.424 
148.94 
162.72 
30.15 
30.11 
30.30 
30.35 
30.35 
13059. .< 
120. 



1.271 

1 .125 
0.565 



(b) 110 Percent of design speed 

READING HUMBER 0498 0497 0496 049S 0494 

IGV TOTAL PRESSURE RATIO 0.999 .1.998 0.998 0.998 0.998 

ROTOR TOTAL PRESSURE RATIO 1.535 1.504 1.444 1.364 1.317 

STATOR TOTAL PRESSURE RATIO 0.980 0.989 0.982 0.969 0.945 

IGV TOTAL TEMPERATURE RATIO 1.000 1.000 1.000 0.999 0.999 

ROTOR TOTAL TEMPERATURE RATIO 1.151 1.145 1.132 1.121 1.113 

STATOR TOTAL TEHPERATURE RATIO 0.996 C.996 0.997 0.996 0.995 

ROTOR ADIABATIC EFFICIENCY 0.865 0.855 0.835 0.768 0.728 

ROTOR MOMENTUM-RISE EFFICIENCY 0.893 0.889 0.856 0.796 0.753 

ROTOR HEAD-RISE COEFFICIENT 0.427 0.404 0.357 0.297 0.260 

FLOW COEFFICIENT 0.381 0.416 0.438 ".445 0.446 

AIRFLOW PER UIIIT FRONTAL AREA 126.57 136.15 142.47 H4.44 144.82 

AIRFLOW PER UNIT ANNULUS AREA 138.29 148.74 155.66 157.81 158.22 

AIRFLOW AT ORIFICE 25.65 27.59 28.88 29.28 29.35 

AIRFLOW AT IGV INLET 25.62 27.57 28.83 29.17 29.25 

AIRFLOW AT ROTOR INLET 25.83 27.77 29.01 29.36 29.44 

AIRFLOW AT ROTOR OUTLET 25.44 27.14 28.61 28.97 29.74 

AIRFLOW AT STATOR OUTLET 25.63 27.57 27.97 28.13 29.10 

ROTATIVE SPEED 11980.8 11964.4 11987.6 11965.0 11979.2 

PERCENT OF DESIGN SPFED 110.1 109.9 110.1 109.9 110.0 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIC 
STAGE ADIABATIC EFFICIENCY 



1.502 
1.146 

0.841 



1.485 
1.139 
0.859 



1.415 
1.128 
0.812 



1.319 
1.115 
0.718 



1.243 
! .106 
0.608 



(c) 100 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0492 


0491 


0490 


0489 


0488 


0.999 


0.999 


0.998 


0.998 


0.998 


1.413 


1.412 


1.383 


1.322 


1.271 


0.989 


0.987 


0.985 


0.976 


0.951 


1.000 


0.999 


0.999 


0.999 


0.999 


1.119 


1.116 


1.109 


1.101 


1.093 


0.998 


0.997 


0.998 


0.997 


0.996 


0.873 


0.896 


0.894 


0.819 


0.762 


0.898 


0.930 


0.918 


0.846 


0.778 


0.400 


0.398 


0.371 


0.315 


0.266 


0.379 


0.416 


0.445 


0.466 


0.469 


115.71 


125.67 


133.34 


138.66 


139.60 


126.42 


137.31 


145.68 


151.49 


152.51 


23.45 


25.47 


27.03 


28.10 


28.29 


23.43 


25.42 


26.9/ 


28.03 


28.21 


23.53 


2S.57 


27.13 


28.19 


28.3' 


22.91 


25.23 


26.76 


27.64 


28.47 


23.16 


25.04 


26.15 


27.04 


27.64 


10898.7 


10895.4 


10898.2 


10886.0 


10900.9 


100.1 


100.1 


100.1 


100.0 


100.1 


1 .396 


1.392 


1.360 


1.238 


1.206 


1 117 


1.112 


1.106 


1.097 


1 .088 


0.857 


0.886 


0.866 


0.771 


0.624 



16 



TABLE II. - Concluded. OVERALL PERFORMANCE OF STAGE 57M2B 



(d) 90 Percent of design speed 

READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
16V TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOHEHTUH-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOW PER UHIT FRONTAL AREA 
AIRFLOW PER UNIT AHNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



101 



0507 
0.999 
1 .317 
0.991 
0.999 
1 .096 
0.998 
0.854 
0.898 

.383 

.364 
.10 
10.45 
20.49 
20.48 
20.59 
20.11 
20.24 
9779.5 

89.8 



1.304 
1.093 
0.849 



(e) 80 Percent of design speed 

READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOHEHTUH-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT AHNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0508 


0.999 


1.246 


0.991 


1.000 


1 .075 


0.999 


0.864 


0.905 


0.374 


0.359 


89.77 


98.08 


18.20 


18.20 


18.29 


18.00 


17.88 


8733.8 


80.2 


1.234 


1.073 


0.84S 



(f) 7U Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEHPERATURE RATIO 
STATOR TOTAL TEHPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR HOHEMTUH-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOH PER UHIT AHNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR IHLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0513 


0512 


0511 


0510 


0509 


0.999 


0.999 


0.999 


0.999 


0.999 


1.181 


1.173 


1.160 


1.150 


1.139 


0.993 


0.993 


0.991 


0.981 


0.968 


1 .000 


1.000 


1.000 


0.999 


0.999 


1 .056 


1.052 


1.049 


1.046 


1.043 


0.999 


0.999 


0.999 


0.998 


0.999 


0.870 


0.895 


0.892 


0.892 


0.882 


0.918 


0.952 


0.960 


0.960 


0.946 


0.363 


0.347 


0.321 


0.299 


0.278 


0.363 


0.405 


0.448 


0.488 


0.525 


79.72 


88.63 


97.22 


105.42 


112.73 


87.09 


96.83 


106.22 


115.17 


123.16 


16.16 


17.96 


19.71 


21 .37 


22.85 


16.15 


17.93 


19.71 


21.31 


22.79 


16.24 


18.03 


19.80 


21.42 


22.87 


15.93 


17.74 


19.32 


21.12 


22.75 


15.78 


17.28 


18.95 


20.34 


21.96 


'614.4 


7618.1 


7624.1 


7620.1 


7613.7 


69.9 


70.0 


70.0 


70.0 


69.9 


1.172 


1 .164 


1.149 


1.127 


1 .102 


1.054 


1 .051 


1.047 


1.043 


1 .041 


0.855 


0.879 


0.865 


0.800 


0.685 



(g) 60 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEHPERATURE RATIO 
ROTOR TOTAL TEHPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR r.OUENTUH-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOH PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANHULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COHPRESSOR PERFORHANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEHPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0514 
1.000 
1.130 
0.995 
1.000 
1.040 
0.999 
0.880 
0.926 
0.349 
0.369 
70.34 
76.85 
14.26 
14.28 
14.38 
14.03 
13.81 
6582.0 

60.5 



1.124 
1 .040 
0.860 



17 



OVKKAU, PERFORMANCE OF STAGE 57M2C 



(a) 12u Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR AOIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE AOIABATIC EFFICIENCT 



0S54 


0553 


0552 


0551 


0550 


0.992 


0.989 


0.988 


0.988 


0.988 


1.402 


1.572 


1.514 


1.443 


1 .404 


0.988 


0.97S 


0.958 


0.943 


0.929 


0.999 


0.999 


0.998 


0.998 


0.999 


1.187 


1.178 


1.149 


1 .159 


1.148 


0.994 


0.994 


0.993 


0.993 


0.994 


0.770 


0.775 


0.747 


0.720 


0.493 


0.804 


0.794 


0.749 


0.739 


0.708 


0.410 


0.389 


0.355 


0.321 


0.282 


0.401 


0.424 


0.427 


0.428 


0.429 


142.19 


148.73 


149.59 


150.04 


150.19 


1SS.35 


142.50 


143.43 


143.93 


144.09 


28.82 


30.15 


30.32 


30.41 


30.44 


28.78 


30.11 


30.21 


30.28 


30.33 


28.95 


30.12 


30.25 


30.33 


30.34 


28.31 


30.04 


30.42 


31.30 


31.25 


29.14 


29.42 


29.17 


29.25 


30.54 


13042.3 


13058.9 


13017.5 


13018.9 


13035.4 


120.0 


120.0 


119.4 


119.4 


119.7 


1.570 


1.515 


1.433 


1.344 


1.291 


1.181 


1.172 


1.159 


1.150 


1.142 


0.741 


0.733 


0.482 


0.420 


5.532 



(b) 110 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR AOIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0S24 
0.994 
1.528 
0.994 
1.000 
1.159 
0.997 
0.812 
0.849 
0.424 
0.411 
134.82 
147.29 
27.33 
27.31 
27.52 
24.19 
27.30 
11973.7 
110.0 



1.510 
1.155 

0.805 



0525 
0.992 
1.513 
0.987 
0.999 
1.154 
0.997 
0.814 
0.847 
0.414 
0.434 
141.01 
154.04 
28.58 
28.57 
28.74 
27.79 
28.09 
11971. 4 
110.0 



1.482 
1.149 
0.797 



0524 
0.991 
1.474 
0.975 
0.999 
1.148 
0.995 
0.795 
0.829 
0.384 
0.449 
145.32 
158.77 
29.44 
29.34 
29. SO 
29.01 
28.43 
11948.3 
109.9 



1.424 
1.141 
0.753 



0523 
0.990 
1.421 
0.957 
0.999 
1.138 
0.995 
0.744 
0.800 
0.344 
0.452 
144.37 
159.91 
29.47 
29.54 
29.44 
30.02 
28.43 
11951.3 
109.8 



1.347 
1.131 
0.477 



0522 
0.989 
1.340 
0.934 
0.999 
1.128 
0.994 
0.719 
0.759 
.294 
.454 



144.83 
140.42 
29.74 
29.44 
29.75 
30.32 
30.04 
11944.9 
109.9 



1.240 
1.122 
0.559 



(c) 100 Percent of design 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE AOIABATIC EFFICIENCT 



0521 


0520 


0519 


0518 


0517 


0.997 


0.995 


0.994 


0.993 


0.992 


1.440 


1.444 


1.418 


1.370 


1.314 


0.987 


0.990 


0.988 


0.948 


0.944 


0.999 


1.000 


0.999 


0.999 


0.999 


1.129 


1.128 


1.122 


1.115 


1.105 


0.998 


0.997 


0.998 


0.994 


0.998 


0.849 


0.870 


0.858 


0.818 


0.774 


0.884 


0.910 


0.895 


0.855 


0.813 


0.429 


0.434 


0.407 


0.343 


0.310 


0.390 


0.432 


0.457 


0.478 


0.482 


118.54 


129.57 


134.38 


141.41 


142.51 


129.53 


141.54 


149.00 


154.50 


155.49 


24.03 


24.24 


27.44 


28.44 


28.88 


23.98 


24.23 


27.54 


28.57 


28.80 


24.13 


24.37 


27.73 


28.72 


28.94 


23.71 


25.58 


24.88 


28.32 


28.99 


23.77 


25.84 


24.73 


27.40 


28.74 


10848.8 


10873.7 


10874.0 


10844.4 


1088S.8 


99.8 


99.9 


99.9 


99.8 


100.0 


1.417 


1.424 


1.393 


1.317 


1.234 


1.124 


1 .123 


1.119 


1.110 


1.101 


0.833 


0.844 


0.833 


0.742 


0.411 



18 



TABLE III. - Continued. OVERALL PERFORMANCE OF STAGE 57M2C 



READING NUMBER 
I6V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



percent of 


design speed 








0547 


0544 


054S 


0544 


0543 


0.997 


0.997 


0.995 


0.994 


0.994 


1.338 


1.343 


1.324 


1.302 


1.264 


0.990 


0.987 


0.983 


0.964 


0.945 


0.999 


0.999 


0.999 


0.999 


0.999 


1.103 


1.099 


1.094 


1 .091 


1.086 


0.998 


0.998 


0.998 


0.997 


0.998 


0.844 


0.886 


0.884 


0.858 


0.809 


0.882 


0.921 


0.931 


0.900 


0.860 


0.407 


0.409 


0.389 


0.362 


0.320 


0.388 


0.429 


0.474 


0.504 


0.512 


107.32 


118.12 


128.68 


135.63 


137.53 


117.26 


129.05 


140.59 


148.19 


150.26 


21.75 


23.94 


26.08 


27.49 


27.88 


21.77 


23.91 


26.02 


27.46 


27.76 


21.77 


23.95 


26.10 


27.55 


27.87 


21.45 


23.62 


25.50 


27.44 


27.86 


21.28 


23.16 


24.90 


26.38 


27.11 


9811.3 


9834.3 


9800. S 


9820.5 


9792.0 


90.1 


90.3 


90.0 


90.2 


90.0 


1.321 


1.321 


1.295 


1.248 


1.188 


1 .099 


1 .096 


1.091 


1 .087 


1.082 


0.833 


0.860 


0.843 


0.748 


0.614 



(e) 80 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0542 


0541 


0540 


0539 


0538 


0.998 


0.998 


0.997 


0.994 


0.996 


1.254 


1.253 


1.244 


1.233 


1.214 


0.991 


0.989 


0.983 


0.970 


0.951 


1.000 


1.000 


0.999 


1.000 


0.999 


1.079 


1.076 


1.073 


1.069 


1.044 


0.999 


0.998 


0.997 


0.998 


0.998 


0.848 


0.878 


0.887 


0.891 


0.871 


0.872 


0.915 


0.941 


0.938 


0.934 


0.391 


0.387 


0.374 


0.354 


0.331 


0.370 


0.419 


0.466 


0.507 


0.537 


91.87 


103.33 


113.74 


123.17 


129.18 


100.37 


112.89 


124.26 


134.57 


141.13 


18.62 


20.94 


23.05 


24.97 


24.18 


18.65 


20.94 


23.06 


24.92 


24.14 


18.65 


20.96 


23.08 


24.93 


24.19 


18.28 


20.66 


22.76 


24.73 


24.13 


18.21 


20.10 


21.91 


23.79 


25.24 


8687.5 


8707.8 


8703.0 


8719.2 


8698.7 


79.8 


80.0 


79.9 


80.1 


79.9 


1.241 


1.237 


1.219 


1.190 


1.151 


1.077 


1.073 


1.069 


1 .066 


1 .063 


0.821 


0.853 


0.841 


0.769 


0.647 



(f) 70 percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PEkFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0537 


0536 


0535 


0534 


0533 


0.999 


0.998 


0.998 


0.997 


0.997 


1.191 


1.189 


1.180 


1.171 


1.161 


0.993 


0.991 


0.985 


0.975 


0.960 


1.000 


1.000 


0.999 


0.999 


0.999 


1.061 


1.058 


1.054 


1.052 


1.049 


0.999 


0.998 


0.999 


0.999 


0.999 


0.844 


0.870 


0.889 


0.894 


0.887 


0.864 


0.913 


0.946 


0.951 


0.960 


0.382 


0.377 


0.358 


0.341 


0.321 


0.359 


0.413 


0.471 


0.509 


0.545 


78.87 


90.12 


101.84 


109.80 


116.77 


84.17 


98.44 


111.27 


119.96 


127.57 


15.99 


18.27 


20.64 


22.25 


23.47 


14.00 


18.29 


20.66 


22.22 


23.40 


15.99 


18.27 


20.65 


22.25 


23.43 


15.65 


17.99 


20.39 


22.05 


23.52 


15.66 


17.50 


19.69 


21 .25 


22.44 


7620.5 


7429.3 


7631.8 


7636.2 


7630.4 


70.0 


70.1 


70.1 


70.1 


70.1 


1 .181 


1 .174 


1.159 


1.139 


1 -lit 


1 .060 


1.056 


1 .052 


1 .050 


1.048 


0.817 


0.845 


0.828 


0.760 


0.639 



19 



TABLE III. - Concluded. OVERALL PERFORMANCE OF STAGE 57M2C 



(g) 60 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUfl-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
A1RFL0M PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0530 


0529 


0528 


0527 


0.99? 


0.999 


0.998 


0.998 


1.138 


1.133 


1.124 


1.113 


.995 


0.993 


0.984 


0.970 


1.000 


1.000 


0.999 


0.999 


1.044 


1.041 


1.038 


1.035 


1.000 


0.999 


0.999 


0.999 


0.857 


0.883 


0.898 


0.892 


0.889 


0.951 


0.973 


0.985 


0.374 


0.358 


0.335 


0.307 


0.354 


0.433 


0.496 


0.551 


67.74 


81.69 


93.20 


102.84 


74.03 


89.25 


101.83 


112.36 


13.73 


16.56 


18.89 


20.84 


13.75 


16.58 


18.86 


20.79 


13.84 


16.64 


18.91 


20.87 


13.51 


16.27 


18.70 


20.69 


13.43 


15.86 


18.08 


19.98 


6559.6 


6561.0 


6562.0 


6560.9 


60.3 


60.3 


60.3 


60.3 


1.131 


1.123 


1.104 


1.077 


1 .044 


1.040 


1 .036 


1.034 


0.822 


0.854 


0.794 


0.639 



20 



TABLE IV. - OVERALL PERFORMANCE OF STAGE 57M2D 



(a) 120 Percent of design speed 



READIH6 MUMBER 
ISV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOHEIiTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOM COEFFICIENT 
AIRFLOU PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT AHNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0578 


0577 


0576 


0575 


0574 


0.981 


0.974 


0.973 


0.971 


0.971 


1.646 


1.597 


1.541 


1.459 


1.401 


0.965 


0.958 


0.945 


0.949 


0.933 


0.999 


0.999 


0.999 


0.999 


0.999 


1.207 


1.197 


1.184 


1.168 


1.159 


0.993 


0.994 


0.997 


1.003 


1.004 


0.739 


0.727 


0.715 


0.676 


0.636 


0.743 


0.726 


0.697 


0.648 


0.619 


0.443 


0.409 


0.372 


0.316 


0.281 


0.395 


0.415 


0.418 


0.417 


0.419 


140.15 


145.82 


147.19 


147.04 


147.23 


153.12 


159.31 


160.81 


160.65 


160.86 


28.41 


29.56 


29.83 


29.80 


29.84 


28.44 


29.61 


29.81 


29.83 


29.83 


28.75 


29.81 


29.95 


29.90 


29.93 


29.14 


30.01 


31.09 


30.53 


30.32 


28.71 


28.50 


28.42 


28.71 


29.99 


13065.5 


13077.5 


13084.0 


13117.3 


13061.9 


120.0 


120.1 


120.2 


120.5 


120.0 


1.557 


1.49! 


1 .417 


1 .344 


1 .270 


1.198 


1.191 


1 .179 


1 .171 


1 .162 


0.682 


0.634 


0.585 


0.515 


0.435 



(b) 110 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEHPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0573 


0572 


0571 


0570 


0569 


0.985 


0.979 


0.977 


0.976 


0.976 


1.558 


1 .530 


1.485 


1.428 


1.364 


0.983 


0.970 


0.959 


0.950 


0.944 


0.999 


0.999 


0.999 


0.999 


0.999 


1.173 


1 .165 


1.158 


1.149 


1.139 


0.996 


.998 


0.997 


0.999 


1.001 


0.783 


0.784 


0.758 


0.720 


0.669 


0.788 


0.769 


0.750 


0.707 


0.659 


0.453 


0.430 


0.395 


0.351 


0.301 


0.414 


0.437 


0.446 


0.448 


0.448 


135.46 


141 .56 


144.18 


144.73 


145.08 


147.99 


154.66 


157.52 


158.12 


158.51 


27.45 


28.69 


29.22 


29.33 


29.41 


27.46 


28.71 


29.20 


29.33 


29.37 


27.80 


29.02 


29.46 


29.54 


29.59 


26.78 


29.04 


29.73 


30.04 


29.70 


27.33 


27.49 


27.69 


28.08 


29.18 


11963.5 


11961 .7 


11969.9 


11979.3 


11983.9 


109.9 


109.9 


110.0 


110.0 


110.1 


1.508 


1.452 


1 .392 


1.324 


1 .256 


1 .167 


1 .161 


1 .154 


1.146 


1.139 


0.744 


0.697 


0.644 


0.573 


0.486 


)0 Percent of design speed 








0568 


0566 


0565 


0564 


0563 


0.989 


0.985 


0.981 


0.979 


0.979 


1.477 


1.464 


1.429 


1.374 


1.329 


0.987 


0.981 


0.968 


0.957 


0.947 


1.000 


0.999 


0.999 


0.998 


0.999 


1.142 


1.136 


1.133 


1.130 


1.119 


0.997 


1 .000 


0.998 


0.994 


0.999 


0.829 


0.847 


0.806 


0.733 


0.709 


0.832 


0.837 


0.799 


0.757 


0.726 


0.466 


0.455 


0.418 


0.348 


0.326 


0.416 


0.453 


0.470 


0.478 


0.479 


125.09 


134.22 


139.39 


141 .66 


141.94 


136.66 


146.64 


152.29 


154.77 


155.08 


25.35 


27.20 


28. 2S 


28.71 


28.77 


25.38 


27.25 


28.28 


28.65 


28.72 


25.59 


27.59 


28.56 


28.89 


28.96 


25.11 


26.75 


28.62 


28.74 


28.82 


25.02 


26.17 


26.92 


27.31 


28.12 


10870.5 


10848.3 


10910.5 


10908.6 


10901.5 


99.9 


99.7 


100.2 


100.2 


100.1 


1 .440 


1 .414 


1 .356 


1.287 


1.232 


1 .138 


1.135 


1 .130 


1.121 


1.117 


0.796 


0.772 


0.699 


0.619 


0.525 



21 



[•ABLE IV. - Concluded. OVERALL PERFORMANCE OF STACK 57M2D 



(d) 



oi design 



READING HUHDER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEHPERATURE RATIO 
ROTOR ADIA3ATIC EFFICIENCY 
ROTOR i:a;iCHTU!1-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT AHHULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



057? 

0.992 

1.354 

0.991 

0.999 

1 .108 

1.000 

0.839 

0.836 

0.430 

0.403 

110.94 

121.21 

22.49 

22.50 

22.55 

22.35 

21.85 

9787.8 

89.9 



1.332 
1.108 
0.793 



(, , ii Percent of design spi ed 

READING NUMBER 0580 

IGV TOTAL PRESSURE RATIO 0.994 

ROTOR TOTAL PRESSURE RATIO 1.274 

STATOR TOTAL PRESSURE RATIO 0.987 

IGV TOTAL TEHPERATURE RATIO 999 

ROTOR TOTAL TEMPERATURE RATIO t .086 

STATOR TOTAL TEMPERATURE RATIO 0.999 

ROTOR ADIABATIC EFFICIENCY 0.834 

ROTOR MOMEHTUM-RISE EFFICIENCY 844 

ROTOR HEAD-RISE COEFFICIENT 0.418 

FLOW COEFFICIENT 0.389 

AIRFLOW PER UNIT FRONTAL AREA 96 56 

AIRFLOW PER UNIT ANNULUS AREA 105 50 

AIRFLOW AT ORIFICE 19.57 

AIRFLOW AT IGV INLET 19.59 

AIRFLOW AT ROTOR INLET 19 61 

AIRFLOW AT ROTOR OUTLET 19.53 

AIRFLOW AT STATOR OUTLET 18.83 

ROTATIVE SPEED 8721 .2 

PERCENT OF DESIGN SPEED 80.1 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1.24? 

STAGE TOTAL TEMPERATURE RATIO 1.084 

STAGE ADIABATIC EFFICIENCY 0.784 



(f) 70 Percent of design speed 

READING NUMBER 0587 0586 0585 0584 0583 

IGV TOTAL PRESSURE RATIO 0.996 0.995 0.993 0.992 0.990 

ROTOR TOTAL PRESSURE RATIO t .205 1.205 1.195 1.188 1.184 

STATOR TOTAL PRESSURE RATIO 0.989 0.985 0.978 0.970 0.960 

IGV TOTAL TEMPERATURE RATIO 1-000 0.999 0.99? 0.999 0.99? 

ROTOR TOTAL TEHPERATURE RATIO 1-065 1.062 1.05? 1.057 1.056 

STATOR TOTAL TEMPERATURE RATIO 0.998 0.998 0.999 1.030 1.000 

R0T03 ADIABATIC EFFICIENCY 0.841 0.878 0.889 0.884 0.875 

ROTOR HOflEMTUH-RISE EFFICIENCY 0.858 0.908 0.921 0.921 0.925 

ROTOR HEAD-RISE COEFFICIENT 0.407 0.405 0.386 0.373 0.365 

FLOW COEFFICIENT 0.393 0.445 0.502 0.532 0.556 

AIRFLOW PER UNIT FRONTAL AREA 86.36 97.68 108.58 114.48 118.93 

AIRFLOH PER UNIT ANHULUS AREA 94.35 106.72 118.63 125.07 129.93 

AIRFLOW AT ORIFICE 17.50 19.80 22.01 23.20 24.10 

AIRFLOW AT IGV INLET 17.54 19.71 22.02 23.18 24.08 

AIRFLOW AT ROTOR INLET 17.48 19.83 22.04 23.22 24.08 

AIRFLOW AT ROTOR OUTLET 17.59 19.87 21.66 22.77 23.67 

AIRFLOW AT STATOR OUTLET '.6.75 18.74 20.79 21.99 23.10 

ROTATIVE SPEED 7666.3 7665.9 7663.3 7656.6 7646.7 

PERCENT OF DESIGN SPEED 70.4 70.4 70.4 70.3 70.2 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1-187 1.180 \ ,\6\ 

STAGE TOTAL TEHPERATURE RATIO 1-063 1.060 1.057 

STAGE ADIABATIC EFFICIENCY 0.805 0.812 0.758 



1.125 
1.056 
0.610 



(g) 60 Percent of design speed 

READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEHPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOHENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOH AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEHPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0588 
0.997 
1.147 
0.992 
1.000 
1.048 
0.998 
0.835 
0.854 
0.397 
0.381 
72.08 
78.75 
14.61 
14.68 
14.65 
14.63 
14.02 
6560.3 

60.3 



1.134 

1.046 
0.803 



22 



TABLE V. - OVERALL PERFORMANCE OF STAGE 57M2E 



(a) 120 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEHPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0606 


0605 


0604 


0603 


0602 


0.994 


0.993 


0.993 


0.993 


0.993 


1.554 


1.461 


1.391 


1.335 


1.270 


0.969 


0.994 


1.004 


0.994 


0.969 


0.999 


0.999 


0.999 


0.999 


0.999 


1.153 


1.139 


1.128 


1.120 


1.105 


0.993 


0.992 


0.992 


0.990 


0.989 


0.879 


0.824 


0.776 


0.718 


0.672 


0.930 


0.908 


0.871 


0.812 


0.744 


0.370 


0.311 


0.266 


0.230 


0.186 


0.347 


0.374 


0.383 


0.385 


0.385 


126.00 


134.31 


136.94 


137.76 


138.08 


137.66 


146.74 


149.62 


150.51 


150.86 


25.54 


27.22 


27.76 


27.92 


27.99 


25.52 


27.20 


27.77 


27.87 


27.95 


25.13 


26.80 


27.39 


27.51 


27.57 


24.65 


25.85 


26.45 


27.10 


28.03 


25.64 


27.22 


27.91 


27.61 


27.40 


13082.1 


13084.2 


13106.6 


13100.8 


13116.9 


120.2 


120.2 


120.4 


120.3 


120.5 


1.497 


1.444 


1.387 


1.318 


1.223 


1.143 


1.128 


1.118 


1.107 


1.093 


0.854 


0.864 


0.831 


0.764 


0.640 



(b) 110 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



READING NUMBER 
I6V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
I6V TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0601 


0600 


0596 


0597 


0599 


0.996 


0.995 


0.994 


0.994 


0.994 


1.446 


1.390 


1.355 


1.299 


1.234 


0.975 


0.991 


0.991 


0.990 


0.973 


1.000 


0.999 


0.999 


0.999 


0.999 


1.126 


1.114 


1.107 


1.100 


1.087 


0.994 


0.993 


0.992 


0.990 


0.990 


0.884 


0.865 


0.848 


0.774 


0.709 


0.943 


0.949 


0.935 


0.877 


0.805 


0.358 


0.314 


0.288 


0.245 


0.193 


0.338 


0.373 


0.392 


0.405 


0.407 


113.55 


123.99 


129.34 


132.94 


133.72 


124.06 


135.47 


141.31 


145.25 


146.10 


23.02 


25.13 


26.22 


26.95 


27.10 


22.99 


25.08 


26.20 


26.92 


27.06 


22.61 


24.73 


25.78 


26.51 


26.65 


22.31 


24.13 


25.49 


26.41 


26.85 


23.01 


24.87 


2S.84 


26.53 


26.43 


11963.2 


11959.5 


11950.2 


11949.4 


11943.3 


109.9 


109.9 


109.8 


109.8 


109.7 


1.404 


1.370 


1.335 


1.278 


1.193 


1.119 


1.105 


1.098 


1.089 


1.076 


0.859 


0.897 


0.881 


0.820 


0.685 


Percent of design speed 








0595 


0594 


0593 


0592 


0591 


0.997 


8.996 


0.995 


0.994 


0.994 


1.358 


1.328 


1.288 


1.255 


1.204 


0.977 


0.987 


0.990 


0.982 


0.974 


1.000 


0.999 


0.999 


0.999 


0.999 


1.104 


1.097 


1.086 


1 .081 


1.073 


0.995 


0.993 


0.995 


0.990 


0.990 


0.883 


0.871 


0.869 


0.823 


0.746 


0.938 


0.950 


0.953 


0.933 


0.858 


0.350 


0.321 


0.282 


0.251 


0.202 


0.330 


0.359 


0.391 


0.419 


0.428 


101.78 


109.94 


118.59 


126.34 


128.76 


111.20 


120.12 


129.57 


138.04 


140.67 


20.63 


22.28 


24.04 


25.61 


26.10 


20.64 


22.28 


24.05 


25.58 


26.04 


20.25 


21.85 


23.63 


25.16 


25.64 


20.13 


21.53 


23.41 


25.39 


25.71 


20.59 


21.97 


23.34 


25.02 


25.33 


10865.3 


10870.4 


10863.2 


10870.9 


0869.7 


99.8 


99.9 


99.8 


99.9 


99.9 


1.323 


1.305 


t.268 


1.226 


1.166 


1.097 


1 .089 


1.080 


1 .070 


1.061 


0.856 


0.888 


0.884 


0.856 


0.736 



23 



lAiUJ V. Concluded. OVERALL PERFORMANCE OF STAGE 57M2E 



(<D 



.■111 ol 



!Bign 



fel SO 



•ni ol design speed 



READING NUMBER 0607 

16V TOTAL PRESSURE RATIO 0.997 

ROTOR TOTAL PRESSURE RATIO 1.282 

STATOR TOTAL PRESSURE RATIO 0.982 

IGV TOTAL TEMPERATURE RATIO 0.999 

ROTOR TOTAL TEMPERATURE RATIO 1.084 

STATOR TOTAL TEMPERATURE RATIO 0.99* 

ROTOR ADIABATIC EFFICIENCY 0.878 

ROTOR MOMENTUM-RISE EFFICIENCY 0.934 

ROTOR HEAD-RISE COEFFICIENT 0.342 

FLOW COEFFICIENT 0.324 

AIRFLOW PER UNIT FRONTAL AREA 90.62 

AIRFLOW PER UNIT ANNULUS AREA 99.00 

AIRFLOW AT ORIFICE 18.37 

AIRFLOW AT IGV INLET 18.38 

AIRFLOW AT ROTOR INLET 18.03 

AIRFLOW AT ROTOR OUTLET 17.97 

AIRFLOW AT STATOR OUTLET 18.31 

ROTATIVE SPEED 9763.0 

PERCENT OF DESIGN SPEED 89.7 



READING NUMBER 0608 

IGV TOTAL PRESSURE RATIO 0.998 

ROTOR TOTAL PRESSURE RATIO 1.211 

STATOR TOTAL PRESSURE RATIO 0.988 

IGV TOTAL TEMPERATURE RATIO 1-000 

ROTOR TOTAL TEMPERATURE RATIO 1-064 

STATOR TOTAL TEMPERATURE RATIO 0.997 

ROTOR ADIABATIC EFFICIENCY 0.877 

ROTOR MOMENTUM-RISE EFFICIENCY 0.934 

ROTOR HEAD-RISE COEFFICIENT 0.328 

FLOW COEFFICIENT 0.325 

AIRFLOW PER UNIT FRONTAL AREA 80.68 

AIRFLOW PER UNIT ANNULUS AREA 88.14 

AIRFLOW AT ORIFICE U.3S 

AIRFLOW AT IGV INLET 16.38 

AIRFLOH AT ROTOR INLET 16.05 

AIRFLOW AT ROTOR OUTLET 15.89 

AIRFLOW AT STATOR OUTLET 1« .19 

ROTATIVE SPEED 8631.0 

PERCENT OF DESIGN SPEED 79.3 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1.255 

STAGE TOTAL TEMPERATURE RATIO 1.078 

STAGE ADIABATIC EFFICIENCY 0.856 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



1.194 
1.060 
0.862 



(f) 70 Percent ol design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0614 


0613 


0612 


0611 


0609 


0.998 


0.998 


0.998 


0.997 


0.997 


1.162 


1.150 


1.135 


1.118 


1.095 


0.991 


0.994 


0,994 


0.993 


0.986 


1.000 


1.000 


1.000 


1 .000 


0.999 


1.050 


1.046 


1.042 


1.037 


1.032 


0.998 


0.998 


0.997 


0.997 


0.996 


0.882 


0.891 


0.881 


0.867 


0.828 


0.931 


0.952 


0.966 


0.966 


0.935 


0.322 


0.299 


0.269 


0.236 


0.191 


0.320 


0.349 


0.385 


0.418 


0.462 


70.84 


76.71 


84.26 


91.14 


100.15 


77.39 


83.81 


92.06 


99.57 


109.41 


14.36 


15.55 


17.08 


18.47 


20.30 


14.38 


15.60 


17.11 


18.53 


20.29 


14.10 


15.29 


16.79 


18.16 


19.90 


13.92 


15.03 


16.71 


18.10 


19.80 


14.19 


15.21 


16.52 


17.86 


19.39 


7637.0 


7629.5 


7632.7 


7631.4 


7620.1 


70.2 


70.1 


70.1 


70.1 


70.0 


1.149 


1.141 


1.125 


1.107 


1.076 


1 .047 


1.043 


1 .038 


1 .033 


1.027 


0.859 


0.890 


0.896 


0.881 


0.770 



(g) 60 Percent of design speed 

READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOHENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



0615 
0.999 
1.113 
0.99S 
1.000 
1.035 
0.998 
0.880 
0.942 
0.307 
0.328 
62.59 
68.39 
12.69 
12.72 
12.47 
12.28 
12.46 
6558.6 
60.2 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



1.106 
1.033 
0.873 



24 



TABLE VI. - OVERALL PERFORMANCE OF STAGE 57M2F 



(a) 120 Percent of design speed 



READING NUMBER 
I6V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
I6V TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOU COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT ICV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESICN SPEED 

COMPRESSOR PERFORMANCE 

STACE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STACE ADIABATIC EFFICIENCT 



READING NUMBER 
I6V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
I6V TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT ICV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0635 


0634 


0633 


0632 


0631 


0.993 


0.991 


0.990 


0.990 


0.990 


1.512 


1.430 


1.324 


1.291 


1.237 


0.961 


0.984 


1.008 


1.046 


0.974 


0.999 


0.999 


0.999 


0.999 


0.999 


1.139 


1.131 


1.112 


1.106 


1.093 


0.994 


0.987 


0.992 


0.992 


0.989 


0.901 


0.819 


0.744 


0.71S 


0.675 


0.949 


0.924 


0.854 


0.833 


0.781 


0.343 


0.292 


0.223 


0.201 


0.165 


0.331 


0.360 


0.372 


0.373 


0.373 


120.67 


129.42 


133.18 


133.59 


133.70 


131.83 


141.40 


145.50 


145.95 


146.08 


24.46 


26.23 


26.99 


27.08 


27.10 


24.44 


26.22 


27.01 


27.06 


27.04 


23.95 


25.71 


26.51 


26.57 


26.58 


23.76 


24.78 


25.85 


25.89 


26.95 


24.44 


26.20 


26.87 


26.91 


26.53 


13049.0 


13048.9 


13048.2 


13041.5 


13035.9 


119.9 


119.9 


119.9 


119.8 


119.7 


1.442 


1.395 


1.320 


1.287 


1.193 


1.131 


1.115 


1.102 


1.096 


1.080 


0.839 


0.865 


0.813 


0.774 


1.643 


ercent of des 


gn speed 








0630 


0629 


0628 


0627 


0626 


0.994 


0.993 


0.992 


0.991 


0.991 


1.418 


1.365 


1.309 


1.275 


1.220 


0.969 


0.985 


0.998 


0.990 


0.972 


0.999 


0.999 


0.999 


0.999 


0.999 


1.117 


1.110 


1.096 


1.093 


1.083 


0.994 


0.989 


0.994 


0.989 


0.987 


0.894 


0.843 


0.836 


0.777 


0.708 


0.962 


0.947 


0.936 


0.910 


0.839 


0.334 


0.294 


0.249 


0.223 


0.180 


0.326 


0.354 


0.376 


0.389 


0.392 


110.03 


118.30 


124.93 


128.70 


129.92 


120.21 


129.24 


136.49 


140.62 


141.94 


22.30 


23.98 


25.32 


26.09 


26.33 


22.31 


24.01 


25.31 


26.10 


26.27 


21.81 


23.50 


24.81 


25.62 


25.78 


21.64 


22.94 


23.81 


25.44 


26.14 


22.19 


23.82 


24 94 


25.71 


25.69 


11985.6 


11981.1 


11990.0 


11998.9 


11984.5 


110.1 


110.1 


110.1 


110.2 


110.1 


1.36S 


1.335 


1.296 


1.251 


1.175 


1.110 


1.097 


1.088 


1.079 


1.068 


0.844 


0.883 


0.873 


0.833 


0.700 



(c) 100 Percent of design speed 



READING NUMBER 0625 

IGV TOTAL PRESSURE RATIO '-"S 

ROTOR TOTAL PRESSURE RATIO » -337 

STATOR TOTAL PRESSURE RATIO 0.974 

IGV TOTAL TEMPERATURE RATIO <••"* 

ROTOR TOTAL TEMPERATURE RATIO I-* 91 

STATOR TOTAL TEMPERATURE RATIO °- 994 

ROTOR ADIABATIC EFFICIENCT 0.888 

ROTOR MOMENTUM-RISE EFFICIENCT O-'Sl 

ROTOR HEAD-RISE COEFFICIENT 0.328 

FLOW COEFFICIENT 0.321 

AIRFLOW PER UNIT FRONTAL AREA "-20 

AIRFLOW PER UNIT ANNULUS AREA 108.39 

AIRFLOW AT ORIFICE 20.11 

AIRFLOW AT IGV INLET 20.12 

AIRFLOW AT ROTOR INLET 1?.«7 

AIRFLOW AT ROTOR OUTLET 19.64 

AIRFLOW AT STATOR OUTLET 19.94 

ROTATIVE SPEED 10869.5 

PERCENT OF DESIGN SPEED ".8 



0624 
0.994 
1.302 
0.984 
0.999 
1.091 
0.991 
0.858 
0.958 
0.295 
0.348 



106.82 
116.71 
21.65 
21.65 
21.17 
20.90 
21.39 
10879.3 
99.9 



0621 
0.993 
1.253 
0.995 
0.999 
1.079 
0.994 
0.845 
0.952 
0.248 
0.376 
114.91 
125.54 
23.29 
23.27 
22.80 
22.19 
22.80 
10888.3 
100.0 



0620 
0.992 
1.186 
0.977 
0.999 
1.067 
0.990 
0.753 
0.882 
0.184 
0.412 
124.66 
136.20 
25.27 
25.24 
24.76 
24.85 
24.54 
0888.6 
100.0 



0619 
0.993 
1.233 
0.986 
0.999 
1.075 
0.991 
0.819 
0.962 
0.229 
0.398 
120.68 
131.84 
24.46 
24.47 
23.97 
23.80 
23.83 
10886.4 
100.0 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1-295 

STAGE TOTAL TEMPERATURE RATIO \ .199 

STAGE ADIABATIC EFFICIENCT 0.849 



1.273 

1.081 
0.882 



1.239 
1.072 
0.883 



I .149 
1.054 
0.754 



1.208 
1.064 
0.858 



25 



I! \l.l. I'l KHIKM.WCI <)]■' STAC 



(d 



ol d 



READING NUMBER 
1GV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR AOIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEEO 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0636 
0.994 
1 .265 
0.980 
0.999 
1 .078 
0.994 
0.889 
0.943 
0.320 
0.316 
88.37 
96.55 
17.91 
17.94 
17.55 
17.37 
17.81 
9782.4 
89.9 



1.235 

1.074 
0.845 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0637 
0.997 
1 .206 
J. 984 
1.000 
1 .062 
0.997 
0.890 
0.944 
0.315 
0.311 
78.03 
85.25 
15.82 
15.86 
15.50 
15.33 
15.70 
8713.7 
80.0 



1.184 
1 .058 
0.847 



(0 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT tGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



=nt ol design .spied 



0643 


0641 


0640 


0639 


8.998 


0.997 


0.997 


0.996 


1.153 


1.133 


1.116 


1.104 


0.98» 


0.995 


0.995 


0.992 


1.001 


1.000 


1.008 


0.999 


1.046 


1.042 


1.036 


1.033 


0.998 


0.997 


8.998 


0.996 


0.896 


0.875 


0.882 


0.847 


S.94B 


0.979 


1.007 


1 .018 


0.304 


0.267 


0.233 


0.209 


0.308 


0.348 


0.382 


.413 


68.81 


76.39 


83.54 


89.99 


75.17 


83.45 


91.27 


98.32 


13.95 


15.48 


14.93 


18.24 


13. 7* 


IS. 53 


17.00 


18.29 


13.67 


15.18 


14.62 


17.88 


13.44 


14.48 


16.07 


17.55 


13.74 


15.11 


16.39 


17.42 


7431.4 


7627.5 


7621.5 


7631.0 


78. 1 


70.1 


70.0 


70.1 


1.13B 


1.124 


1.107 


1.091 


1.044 


1 .038 


1.033 


1.029 


8.847 


0.886 


0.890 


0.878 



8638 
8.995 
1.083 
0.987 
0.999 
1.028 
0.997 
8.838 
8.968 
8.147 
8.444 
94.34 
195.24 
19.53 
19.55 
19.11 
19.82 
18.78 
7622.5 
70.0 



1.064 
1.023 
0.766 






READING NUMBEK 0644 

IGV TOTAL PRESSURE RATIO 0.998 

ROTOR TOTAL PRESSURE RATIO 1.107 

STATOR TOTAL PRESSURE RATIO 0.993 

IGV TOTAL TEMPERATURE RATIO 1.000 

ROTOR TOTAL TEMPERATURE RATIO 1.033 

STATOH TOTAL TEMPERATURE RATIO 0.998 

ROTOR ADIABATIC EFFICIENCT 0.898 

ROTOR MOMEHTUM-RISE EFFICIENCY 0.955 

ROTOR HEAD-RISE COEFFICIENT 0.294 

FLOW COEFFICIENT 0.317 

AIRFLOW PER UNIT FRONTAL AREA 60.23 

AIRFLOW PER UNIT ANNULUS AREA 65.88 

AIRFLOW AT ORIFICE 12.21 

AIRFLOW AT IGV INLET 12.24 

AIRFLOW AT ROTOR INLET 11.99 

AIRFLOW AT ROTOR OUTLET 11.78 

AIRFLOW AT STATOR OUTLET 11.93 

ROTATIVE SPEED 6525.1 

PERCENT OF DESIGN SPEED S9.9 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPtRATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



1.097 
1.031 
0.855 



26 



OYKRALL Pl'RFORMAXCl OF STAG 



READING NUMBER 0662 

ISV TOTAL PRESSURE RATIO 0.992 

ROTOR TOTAL PRESSURE RATIO 1.466 

STATOR TOTAL PRESSUkE RATIO 0.95S 

IGV TOTAL TEMPERATURE RATIO 0.999 

ROTOR TOTAL TEMPERATURE RATIO 1.133 

STATOR TOTAL TEMPERATURE RATIO 0.990 

ROTOR ADIA3ATIC EFFICIENCY 0.866 

ROTOR MOHENTUM-RISE EFFICIENCT 0.947 

ROTOR HEAD-RISE COEFFICIENT 0.312 

FLOW COEFFICIENT 0.312 

AIRFLOW PER UNIT FRONTAL AREA 115.01 

AIRFLOW PER UHIT ANNULUS AREA 125.65 

23.31 
23.26 
23.20 
22.60 
23.27 
13102.7 
120.4 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO , 309 

STAGE TOTAL TEMPERATURE RATIO J,™ 

STAGE ADIABATIC EFFICIENCT J gt 8 



AIRFLOW 


AT 


ORIFICE 


AIRFLOW 


AT 


IGV INLET 


AIRFLOW 


AT 


ROTOR INLET 


AIRFLOW 


AT 


ROTOR OUTLET 


AIRFLOW 


AT 


STATOR OUTLET 


ROTATIVE 


: SPEED 


PERCENT 


OF 


DESIGN SPEED 



0661 


0660 


0659 


0.990 


0.989 


0.989 


1 .390 


1.319 


1 .259 


0.983 


0.991 


0.999 


.999 


0.999 


0.999 


1.121 


1 .108 


1 .098 


0.988 


0.989 


0.989 


0.815 


0.759 


0.693 


0.909 


0.890 


0.839 


0.264 


0.217 


0.178 


0.333 


0.347 


0.350 


121.77 


126.00 


126.82 


133.03 


137.66 


138.56 


24.68 


25.54 


25.71 


24.64 


25.53 


25.66 


24.62 


25.56 


25.72 


23.36 


24.81 


25.05 


24.84 


25.54 


25.75 


3102.7 


13099.4 


13085.1 


120.4 


120.3 


120.2 


1 .353 


1 .292 


1 .243 


1.107 


1 .094 


1 !08S 
0.754 


0.847 


0.806 



(b) 110 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



(c) 100 Percent of 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



1 . 


218 


. 


970 


. 


999 


1 . 


088 


. 


988 


0. 


663 


. 


781 


0. 


151 


. 


350 


26 


,.99 


3£ 


1.74 


25 


, .74 


25 


1. 71 


2< 


,.74 


2« 


,.65 


25 


,.22 


082.7 


120.2 


1 . 


163 


1 . 


073 





622 



0657 


0656 


0655 


0654 


0653 


0.995 


0.993 


0.992 


0.991 


0.990 


1.372 


1.330 


1 .281 


1 .242 


1.192 


0.966 


0.983 


0.994 


0.986 


0.980 


0.999 


0.999 


0.999 


0.999 


0.999 


1 .110 


1.101 


1 .089 


1 .084 


1 .073 


0.991 


0.992 


0.994 


0.988 


0.989 


0.858 


0.840 


0.822 


0.765 


0.700 


0.947 


0.930 


0.922 


0.926 


0.841 


0.303 


0.269 


0.230 


0.200 


0.159 


0.310 


0.327 


0.345 


0.364 


0.369 


04.73 


110.06 


115.41 


120.80 


122.40 


.14.43 


120.24 


126.09 


131 .98 


133.73 


21 .23 


22.31 


23.39 


24.49 


24.81 


21 .21 


22.27 


23.41 


24.48 


24.81 


21 .08 


22.19 


23.39 


24.48 


24.83 


20.56 


21 .26 


22.20 


24.01 


24.49 


2! .15 


22.32 


23.29 


24.21 


24.41 


916.5 


11919.8 


11933.0 


11905.1 


11915.9 


109.5 


109.5 


109.6 


109.4 


109.5 


1 .319 


1 .299 


1 .264 


1 .213 


1 .156 


1 .099 


1 .091 


1 .081 


1 .070 


1 .060 


0.830 


0.854 


.851 


.816 


0.706 



0652 


0651 


0650 


0649 


0648 


0.996 


0.995 


0.994 


0.992 


0.991 


1.310 


1 .267 


1.222 


1.196 


1 .159 


0.968 


0.985 


0.992 


0.985 


.977 


.999 


0.999 


0.999 


0.999 


0.998 


1 .092 


1 .083 


1 .072 


1 .067 


1 .058 


0.993 


0.992 


0.993 


0.990 


0.991 


0.868 


0.839 


0.815 


0.788 


0.744 


0.944 


0.929 


0.936 


0.936 


0.890 


0.304 


0.263 


0.220 


0.195 


0.158 


0.303 


0.327 


0.353 


0.373 


0.386 


93.96 


100.60 


107.92 


113.58 


117.38 


102.65 


109.91 


117.91 


124.09 


128.24 


19.04 


20.39 


21 .87 


23.02 


23.79 


19.03 


20 .44 


21 .89 


23.03 


23.73 


18.91 


20.31 


21 .83 


23.00 


23.69 


18.49 


19.53 


21 .00 


22.72 


23.55 


18.91 


20.36 


21 .59 


22.61 


23.05 


10851 .4 


10848.2 


10841 .6 


10844.8 


10847.7 


99.7 


99.7 


99.6 


99.6 


99.6 


1 .263 


1 .242 


1 .206 


1 .170 


1 .123 


1 .084 


1 .074 


1 .064 


1 .056 


1 .046 


0.819 


0.861 


0.861 


0.825 


0.728 



27 



(I. OVERALL PERFORMANCE OF STAGE :,7M2<; 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0667 


0666 


0665 


0664 


0663 


0.997 


0.996 


0.995 


0.994 


0.993 


1.252 


1 .204 


1 .179 


1 .157 


1.128 


0.974 


0.993 


0.995 


0.986 


0.981 


1 .000 


0.999 


0.999 


.999 


0.999 


1 .076 


1 .064 


1.058 


1 .053 


1 .04S 


0.99S 


0.996 


0.995 


0.993 


0.993 


0.869 


0.850 


0.834 


0.804 


0.773 


0.933 


0.931 


0.946 


0.947 


0.914 


0.301 


0.244 


0.215 


0.189 


0.155 


0.295 


0.333 


0.354 


0.380 


0.396 


83.76 


93.34 


98.97 


105.63 


109.80 


91.51 


101 .98 


108.13 


115.41 


119.96 


16.98 


18.92 


20.06 


21 .41 


22.26 


16.97 


18.96 


20.09 


21 .42 


22.23 


16.86 


18.86 


19.98 


21 .35 


22.17 


16.36 


17.99 


19.29 


21 .20 


22.15 


16.89 


18.78 


19.82 


20.89 


21 .58 


9843.6 


9841 .5 


9831 .5 


9837.7 


9831 .9 


90.4 


90.4 


90.3 


90.4 


90.3 


1 .215 


1 .190 


1 .167 


1 .134 


1.100 


1 .071 


1 .059 


1.052 


1 .044 


1 .037 


0.810 


0.869 


0.871 


0.829 


0.745 



(e) SO Percent ol design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATI 
STATOR TOTAL PRESSURE RAT 
IGV TOTAL TEMPERATURE RAT 
ROTOR TOTAL TEMPERATURE R 
STATOR TOTAL TEMPERATURE 
ROTOR ADIABATIC EFFICIENC 
ROTOR MOMENTUM-RISE EFFIC 
ROTOR HEAD-RISE COEFFICIE 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL 
AIRFLOW PER UNIT ANNULUS 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RAT 
STAGE ADIABATIC EFFICIENCY 



ATIO 
RATIO 



AREA 
AREA 



0674 


0673 


0670 


0669 


0.997 


0.996 


0.996 


0.995 


1.198 


1.153 


1.134 


1.115 


0.978 


0.995 


0.991 


0.988 


1 .000 


1 .000 


1.000 


0.999 


1.061 


1.049 


1 .044 


1.039 


0.996 


0.997 


0.995 


0.995 


0.869 


0.850 


0.824 


0.820 


0.929 


0.935 


0.959 


0.953 


0.302 


0.234 


0.206 


0.177 


0.294 


0.344 


0.366 


0.389 


74.16 


85.87 


90.99 


96.23 


81 .02 


93.81 


99.41 


105.14 


IS. 03 


17.40 


18.44 


19.51 


15.07 


17.46 


18.49 


19.55 


14.86 


17.26 


18.34 


19.46 


14.50 


16.58 


18.03 


19.34 


14.83 


17.07 


17.99 


18.91 


8717.3 


8715.4 


8704.6 


8697.9 


80.1 


80.1 


80.0 


79.9 


1.168 


1 .143 


1 .119 


1 .096 


1 .056 


1 .045 


1 .038 


1 .032 


0.807 


0.862 


0.857 


0.820 



0668 
0.995 
1 .096 
0.984 
0.999 
1.033 
0.995 
0.799 
0.925 
0.149 
0.40S 
100.14 
109.40 
20.30 
20.29 
20.21 
20.17 
19.52 
3704.2 
80.0 



1 .074 
1 .028 
0.739 



(f) 70 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0685 


0684 


0683 


0682 


0680 


0.998 


0.997 


0.997 


0.996 


0.996 


1.147 


1 .119 


1.107 


1 .090 


1.076 


0.985 


.994 


0.993 


0.991 


0.987 


1.000 


1.0011 


1 .000 


1 .000 


0.999 


1.046 


1.038 


1.035 


1.029 


1 .026 


0.997 


0.998 


0.996 


0.997 


0.997 


0.869 


0.861 


0.835 


0.846 


0.820 


0.930 


0.936 


0.956 


0.950 


0.926 


0.293 


0.238 


0.21S 


0.179 


0.152 


0.297 


0.339 


0.368 


0.400 


0.421 


65.97 


74.86 


80.73 


87.48 


91 .99 


72.07 


81 .78 


88.20 


95.58 


100.51 


13.37 


15.17 


16.36 


17.73 


18.65 


13.38 


15.22 


16.42 


17.81 


18.68 


13.26 


15.06 


16.24 


17.62 


18.52 


12.95 


14.44 


15.96 


17.51 


18.50 


13.21 


14.86 


15.82 


17.10 


17.86 


7642.7 


7650.9 


7635.5 


7648.7 


7649.5 


70.2 


70.3 


70.1 


70.3 


70.3 


1.128 


1.112 


1.096 


1.076 


1.058 


1 .043 


1 .036 


1 .031 


1 .026 


1.022 


0.821 


0.868 


0.858 


0.820 


0.742 



2s 



TABLE VII. - Concluded. OVERALL PERFORMANCE OF STAGE 57M2G 



Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



067? 


0678 


0677 


0676 


0675 


0.999 


0.998 


0.998 


0.997 


0.997 


1.106 


1.087 


1.076 


1.062 


1.049 


0.989 


0.997 


0.993 


0.992 


0.989 


1.000 


1.000 


1.000 


1.000 


1.000 


1.033 


1.028 


1.025 


1.020 


1.017 


0.998 


0.999 


0.997 


0.998 


0.998 


0.871 


0.861 


0.836 


0.854 


0.808 


0.930 


0.941 


0.963 


0.953 


0.920 


0.289 


0.237 


0.208 


0.170 


0.136 


0.294 


0.334 


0.374 


0.410 


0.435 


SS.88 


63.38 


70.52 


76.90 


81.28 


61.06 


69.24 


77.04 


84.02 


88.80 


11.33 


12.85 


14.29 


15.59 


16.47 


11.35 


12.89 


14.35 


15.66 


16.54 


11.28 


12.77 


14.19 


15.47 


16.33 


11.01 


12.29 


14.04 


15.44 


16.36 


11.17 


12.56 


13.74 


14.96 


15.76 


5522.9 


6528.8 


6518.6 


6526.9 


6511.9 


59.9 


60.0 


59.9 


60.0 


59.8 


1.092 


1.081 


1.066 


1.051 


1 .034 


1.031 


1 .026 


1.022 


1.018 


1.014 
0.669 


0.813 


0.856 


0.843 


0.788 



29 



TABLK VIII. - OVKKALL PERPORMANCJ 01 STAGI , 



(a) 120 P 

reading number 
igv total pressure ratio 
rotor total pressure ratio 
stator total pressure ratio 
igv total temperature ratio 
rotor total temperature ratio 
stator total temperature ratio 
rotor ad1abatic efficiency 
rotor momentum-rise efficiency 
rotor head-rise coefficient 
flow coefficient 
airflow per unit frontal area 
airflow per unit annulus area 
airflow at orifice 
airflow at igv inlet 
airflow at rotor inlet 
airflow at rotor outlet 
airflow at stator outlet 
rotative speed 
percent of design speed 

compressor performance 

stage total pressure ratio 
stage total temperature ratio 
stage adiabatic efficiency 



ni oi design .spec 



0704 


0703 


0702 


0701 


0700 


0.981 


0.978 


0.975 


0.974 


0.974 


1 .437 


1.401 


1.333 


1.250 


1.188 


0.952 


0.957 


0.974 


0.994 


1.000 


0.998 


0.998 


0.998 


0.998 


0.998 


1 .122 


1.117 


1 .106 


1 .094 


1 .085 


0.997 


0.989 


0.988 


0.989 


0.989 


0.896 


0.864 


0.804 


0.700 


0.593 


0.980 


0.994 


0.957 


0.879 


0.819 


0.292 


0.270 


0.226 


0.172 


0.131 


0.297 


0.314 


0.327 


0.334 


0.33S 


109.84 


115.02 


119.41 


121 .67 


122.11 


120.00 


125.66 


130.46 


132.93 


133.42 


22.26 


23.31 


24.20 


24.66 


24.75 


22.23 


23.31 


24.20 


24.64 


24.72 


21 .78 


22.87 


23.72 


24.24 


24.32 


21 .74 


23.07 


23.53 


23.20 


23.09 


22.40 


23.41 


24.31 


24.55 


24.52 


13089.9 


13079.1 


13084.5 


13086.9 


13078.4 


120.2 


120.1 


120.2 


120.2 


120.1 


1.343 


1.311 


1.266 


1.210 


1.157 


1.116 


1.103 


1.091 


1 .080 


1 .071 


0.755 


0.781 


0.765 


0.701 


0.600 



(b) 110 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0699 


0698 


0697 


0696 


069S 


0.985 


0.983 


0.981 


0.977 


0.976 


1 .360 


1.335 


1.291 


1.204 


1.163 


0.960 


0.965 


0.975 


0.995 


0.998 


0.999 


0.999 


0.998 


0.998 


0.998 


1 .103 


1.099 


1.091 


1.076 


1.070 


0.996 


0.992 


0.990 


0.990 


0.990 


0.891 


0.873 


0.829 


0.711 


0.628 


0.972 


0.994 


0.971 


0.918 


0.865 


0.288 


0.269 


0.235 


0.167 


0.134 


0.295 


0.310 


0.327 


0.347 


0.352 


100.60 


105.38 


110.44 


116.43 


118.01 


109.91 


115.13 


120.66 


127.20 


128.93 


20.39 


21.36 


22.39 


23.60 


23.92 


20.39 


21.35 


22.40 


23.61 


23.92 


19.91 


20.92 


21.85 


23.07 


23.36 


19.82 


21.06 


21.91 


22.13 


22.39 


20.45 


21.28 


22.35 


23.22 


23.56 


1988.7 


11992.0 


11983.5 


11982.8 


11984.1 


110.1 


110.2 


110.1 


110.1 


110.1 


1.286 


1.266 


1.235 


1.170 


1.134 


1 .098 


1.089 


1.079 


1.064 


1 .057 


0.762 


0.787 


0.791 


0.717 


0.637 



(c) 100 Percent of design speed 

READING NUMBER 0694 0693 0692 

I6V TOTAL PRESSURE RATIO 0.988 0.986 0.984 

ROTOR TOTAL PRESSURE RATIO 1.293 1.256 1.220 

STATOR TOTAL PRESSURE RATIO 0.966 0.973 0.982 

IGV TOTAL TEMPERATURE RATIO 0.999 0.999 0.999 

ROTOR TOTAL TEMPERATURE RATIO 1.085 1.078 1.072 

STATOR TOTAL TEMPERATURE RATIO 0.997 0.992 0.991 

ROTOR ADIABATIC EFFICIENCY 0.894 0.862 0.811 

ROTOR MOMENTUM-RISE EFFICIENCY 0.978 0.987 0.960 

ROTOR HEAD-RISE COEFFICIENT 0.285 0.251 0.217 

FLOW COEFFICIENT 0.293 0.321 0.337 

AIRFLOW PER UNIT FRONTAL AREA 91.33 99.23 103.60 

AIRFLOW PER UNIT ANNULUS AREA 99.78 108.41 1-13.19 

AIRFLOW AT ORIFICE 18.51 20.11 21.00 

AIRFLOW AT IGV INLET 18.50 20.15 21.04 

AIRFLOW AT ROTOR INLET 17.92 19.63 20.56 

AIRFLOW AT ROTOR OUTLET 18.00 19.99 20.31 

AIRFLOW AT STATOR OUTLET 18.42 19.98 20.68 

ROTATIVE SPEED 10877.8 10875.1 10867.0 

PERCENT OF DESIGN SPEED 99.9 99.9 99.8 



0691 
0.981 
1.169 
0.996 
0.998 
1 .062 
0.992 
0.733 
0.923 
0.167 
0.353 
108.20 
118.21 
21.93 
21.95 
21.46 
20.43 
21.46 
10869.3 
99.8 



0690 
0.980 
1.133 
0.999 
0.999 
1.056 
0.991 
0.648 
0.900 
0.132 
0.364 
111.38 
121.69 
22. S7 
22.59 
22.12 
21.07 
22.13 
10873.2 

99.9 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1.235 » -204 1.179 1.143 1.110 

STAGE TOTAL TEMPERATURE RATIO 1.081 J -Off 1.0M 1-0S2 1.045 

STAGE ADIABATIC EFFICIENCY 0.766 ".800 0.791 0.742 0.665 



30 



TABLE VIE. - Concluded. OVERALL PEKEORM ANCE OF STAGE f,7M2H 



(d) 90 Percent of design speed 

READING NUMBER 
ICV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
ISV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRCNTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



070S 
0.991 
t.229 
0.973 
0.999 
1.068 
0.998 
0.894 
0.974 
0.279 
0.292 
82.08 
89.68 
16.64 
16.63 
16.17 
16.16 
16.67 
9730.4 
89.4 



1.185 
1.064 
0.770 



(e) 80 Percent of design speed 

READING NUMBER 0706 

IGV TOTAL PRESSURE RATIO 0.993 

ROTOR TOTAL PRESSURE RATIO 1.180 

STATOR TOTAL PRESSURE RATIO 0.979 

IGV TOTAL TEMPERATURE RATIO 999 

ROTOR TOTAL TEMPERATURE RATIO 1.054 

STATOR TOTAL TEMPERATURE RATIO 0.998 

ROTOR ADIABATIC EFFICIENCY 0.895 

ROTOR MOMENTUM-RISE EFFICIENCY 0.985 

ROTOR HEAD-RISE COEFFICIENT 0.274 

FLOW COEFFICIENT 0.294 

AIRFLOW PER UNIT FRONTAL AREA 74.07 

AIRFLOW PER UNIT ANNULUS AREA 80 93 

AIRFLOW AT ORIFICE 15.01 

AIRFLOW AT IGV INLET 15.02 

AIRFLOW AT ROTOR INLET 14 .50 

AIRFLOW AT ROTOR OUTLET 14.68 

AIRFLOW AT STATOR OUTLET 14.92 

ROTATIVE SPEED 8714 1 

PERCENT OF DESIGN SPEED 80.0 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1 147 

STAGE TOTAL TEMPERATURE RATIO i 051 

STAGE ADIABATIC EFFICIENCY 0.783 



(f) 70 Percent of design speed 



READING NUMBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR MOMENTUM-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOW AT ROTOR INLET 
AIRFLOW AT ROTOR OUTLET 
AIRFLOW AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



0711 


0710 


0709 


0708 


0707 


0.995 


0.994 


0.992 


0.991 


0.989 


1.144 


1.125 


1.097 


1.075 


1.060 


0.981 


0.987 


0.994 


0.997 


0.996 


1.000 


0.999 


0.999 


0.999 


0.999 


1.044 


1.039 


1.033 


1.028 


1.025 


0.999 


0.997 


0.996 


0.996 


0.996 


0.897 


0.885 


0.811 


0.736 


0.680 


0.962 


0.999 


0.974 


0.968 


0.953 


0.282 


0.245 


0.191 


0.148 


0.119 


0.280 


0.319 


0.352 


0.377 


0.394 


62.55 


71.02 


78.00 


83.17 


86.69 


68.33 


77.60 


85.22 


90.87 


94.72 


12.68 


14.40 


15.81 


16.86 


17.57 


12.71 


14.42 


15.86 


16.90 


17.62 


12.28 


13.94 


15.33 


16.31 


17.01 


12.31 


14.21 


15.08 


15.97 


16.80 


12.60 


14.22 


15.38 


16.33 


16.98 


7696.9 


7698.7 


7696.0 


7687.5 


7690.7 


70.7 


70.7 


70.7 


70.6 


70.6 


1.117 


1.103 


1.081 


1.062 


1.044 


1.042 


1.034 


1.029 


1.024 


1.019 


0.760 


0.828 


0.791 


0.730 


0.652 



(g) 60 Percent of design speed 

READING NUMBER 0712 

IGV TOTAL PRESSURE RATIO 0.996 

ROTOR TOTAL PRESSURE RATIO 1.101 

STATOR TOTAL PRESSURE RATIO t.988 

IGV TOTAL TEMPERATURE RATIO 1.000 

ROTOR TOTAL TEMPERATURE RATIO 1.031 

STATOR TOTAL TEMPERATURE RATIO 0.999 

ROTOR ADIABATIC EFFICIENCY 0.899 

ROTOR MOMENTUM-RISE EFFICIENCT 0.982 

ROTOR HEAD-RISE COEFFICIENT 0.269 

FLOW COEFFICIENT 0.289 

AIRFLOW PER UNIT FRONTAL AREA 56.01 

AIRFLOW PER UNIT ANNULUS AREA 61.20 

AIRFLOW AT ORIFICE 11 .35 

AIRFLOW AT IGV INLET 11.35 

AIRFLOW AT ROTOR INLET 10.94 

AIRFLOW AT ROTOR OUTLET 11.12 

AIRFLOW AT STATOR OUTLET 11.27 

ROTATIVE SPEED 6615.9 

PERCENT OF DESIGN SPEED 60.8 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



.084 
.030 
.783 



31 



TABLE ix. - ovi:kai,l pkkfokmanck of STAGE :.7M2i 



(a) 120 Percent of design speed 



READING NUMBER 
I6V TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCT 
ROTOR MOMENTUM-RISE EFFICIENCT 
ROTOR HEAD-RISE COEFFICIENT 
FLOW COEFFICIENT 
AIRFLOH PER UNIT FRONTAL AREA 
AIRFLOW PER UNIT ANNULUS AREA 
AIRFLOH AT ORIFICE 
AIRFLOW AT IGV INLET 
AIRFLOH AT ROTOR INLET 
AIRFLOH AT ROTOR OUTLET 
AIRFLOH AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCT 



0729 
0.967 
1 .403 
0.933 
0.999 
1.112 
1.000 
0.904 
0.964 
0.269 
0.262 
98.05 
107.12 
19.87 
19.84 
19.60 
19.04 
19.50 
13101.6 
120.4 



1.245 
1.111 
0.427 



0728 
0.963 
1.363 
0.946 
0.999 
1.103 
1.000 
0.900 
0.974 
0.243 
0.273 
101.89 
111.32 
20.65 
20.41 
20.32 
19.71 
20.48 
13103.2 
120.4 



0727 
9.959 
1.301 
0.948 
0.999 
1.091 
0.999 
0.854 
0.995 
0.203 
0.284 
104.17 
114.00 
21.52 
21.48 
21.23 
20.41 
21.54 
13094.3 
120.3 



1.208 
1.089 
0.427 



0. 


955 


1 


256 


0. 


9B1 


0. 


998 


1 


086 


0. 


993 


0. 


786 


0. 


983 


0. 


174 


0. 


295 


10a 


.87 


118 


.95 


22 


.07 


22 


.06 


21 


.74 


21 


.46 


22 


.69 


3083.5 


120.2 



1.176 
1.077 
0.418 



0725 
0.953 
1.228 
0.982 
0.998 
1.081 
0.991 
0.745 
0.948 
0.156 
0.298 
110.06 
120.25 
22.31 
22.24 
21.88 
21.71 
22.71 
13092.3 
120.3 



1.149 

1.070 
0.580 



(b) 110 Percent of design speed 

READING NUMBER 0724 0723 0722 0721 0720 

16V TOTAL PRESSURE RATIO 0.971 0.948 0.945 0.943 0.960 

ROTOR TOTAL PRESSURE RATIO 1.322 1.285 1.248 1.217 1.187 

STATOR TOTAL PRESSURE RATIO 0.949 0.943 0.978 0.982 0.980 

IGV TOTAL TEMPERATURE RATIO 0.999 0.999 0.999 0.999 0.999 

ROTOR TOTAL TEMPERATURE RATIO 1.093 1.033 1.078 1.072 1.045 

STATOR TOTAL TEMPERATURE RATIO 0.999 0.999 0.994 0.994 0.992 

ROTOR ADIA3ATIC EFFICIENCT 0.897 0.892 0.839 0.807 0.749 

ROTOR HOMENTUM-RISE EFFICIENCT 0.948 0.981 0.998 1.003 0.971 

ROTOR HEAD-RISE COEFFICIENT 0.259 0.230 0.202 0.177 0.154 

FLOH COEFFICIENT 0.247 0.281 0.294 0.304 0.311 

AIRFLOH PER UNIT FRONTAL AREA 91.55 95.71 99.84 102.83 105.11 

AIRFLOH PER UNIT ANNULUS AREA 100.02 104.57 109.07 112.34 114.83 

AIRFLOH AT ORIFICE 18.54 19.40 20.24 20.84 21.30 

AIRFLOH AT IGV INLET 18.53 19.43 20.23 20.83 21.30 

AIRFLOH AT ROTOR INLET 18.04 19.01 19.85 20.49 20.91 

AIRFLOH AT ROTOR OUTLET 17.70 18.54 19.41 20.33 20.95 

AIRFLOH AT STATOR OUTLET 18.27 19.33 20.45 21.17 21.40 

ROTATIVE SPEED 11941.0 11951.0 11942.4 11937.3 11933. S 

PERCENT OF DESIGN SPEED 109.9 109.8 109.7 109.7 109.4 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1.219 1-197 

STAGE TOTAL TEMPERATURE RATIO 1.090 1 .081 

STAGE ADIABATIC EFFICIENCT 0.447 0.453 



1.178 
1.072 
0.442 



1.151 

1.044 
0.443 



1.117 

1.055 
0.583 



(c) 100 Percent of design speed 

READING NUMBER 0719 0718 0717 0714 0715 

IGV TOTAL PRESSURE RATIO 0.974 0.974 0.971 0.947 0.945 

ROTOR TOTAL PRESSURE RATIO 1.249 1.244 1.212 1.175 1.155 

STATOR TOTAL PRESSURE RATIO 0.954 0.947 0.981 0.983 0.982 

I6V TOTAL TEMPERATURE RATIO 0.999 0.999 0.999 0.999 0.999 

ROTOR TOTAL TEMPERATURE RATIO 1.078 1.071 1.044 1.058 1.054 

STATOR TOTAL TEMPERATURE RATIO 0.998 0.999 0.997 0.994 0.992 

ROTOR ADIABATIC EFFICIENCT 0.904 0.904 0.854 0.808 0.770 

ROTOR MOMEHTUM-RISE EFFICIENCT 0.971 0.989 1.004 1.006 0.985 

ROTOR HEAD-RISE COEFFICIENT 0.259 0.235 0.204 0.171 0.151 

FLOH COEFFICIENT 0.249 0.281 0.295 0.311 0.319 

AIRFLOH PER UNIT FRONTAL AREA 84.82 88.50 92.42 97.08 99.25 

AIRFLOH PER UNIT ANNULUS AREA 92.47 94.49 100.97 104.04 108.44 

AIRFLOH AT ORIFICE 17.19 17.94 18.73 19.48 20.12 

AIRFLOH AT IGV INLET 17.14 17.90 18.71 19.44 20.11 

AIRFLOH AT ROTOR INLET 14.71 17.45 18.32 19.24 19.70 

AIRFLOH AT ROTOR OUTLET 14.34 17.12 17.84 19.13 19.47 

AIRFLOH AT STATOR OUTLET 16.84 17.78 18.83 19.77 20.02 

ROTATIVE SPEED 10947.9 10948.9 10941.2 10931.4 10943.3 

PERCENT OF DESIGN SPEED 100.6 1D0.6 100.5 100.4 100.5 

COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 1.185 1.172 1.154 1.118 1.095 

STAGE TOTAL TEMPERATURE RATIO 1.074 1.049 1.042 1-050 1.045 

STAGE ADIABATIC EFFICIENCT 0.454 0.470 0.477 0.641 0.588 



32 



TABLE EX. - Concluded. OVERALL PERFORMANCE OF STAGE 57M2I 



(d) 90 Percent of design speed 

READING MUHBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
IGV TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEMPERATURE RATIO 
STATOR TOTAL TEHPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR ROHEMTUH-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOW PER UNIT FRONTAL AREA 
AIRFLOH PER U ft I T ANNULUS AREA 
AIRFLOW AT ORIFICE 
AIRFLOH AT IGV INLET 
AIRFLOH AT ROTOR INLET 
AIRFLOH AT ROTOR OUTLET 
AIRFLOH AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



READING NUHBER 
IGV TOTAL PRESSURE RATIO 
ROTOR TOTAL PRESSURE RATIO 
STATOR TOTAL PRESSURE RATIO 
I6V TOTAL TEMPERATURE RATIO 
ROTOR TOTAL TEHPERATURE RATIO 
STATOR TOTAL TEMPERATURE RATIO 
ROTOR ADIABATIC EFFICIENCY 
ROTOR H01IEIITUH-RISE EFFICIENCY 
ROTOR HEAD-RISE COEFFICIENT 
FLOH COEFFICIENT 
AIRFLOH PER UNIT FRONTAL AREA 
AIRFLOH PER UHIT ANNULUS AREA 
AIRFLOH AT ORIFICE 
AIRFLOH AT IGV INLET 
AIRFLOH AT ROTOR INLET 
AIRFLOH AT ROTOR OUTLET 
AIRFLOH AT STATOR OUTLET 
ROTATIVE SPEED 
PERCENT OF DESIGN SPEED 



COMPRESSOR PERFORMANCE 

STAGE TOTAL PRESSURE RATIO 
STAGE TOTAL TEMPERATURE RATIO 
STAGE ADIABATIC EFFICIENCY 



(d) (e) 80 Percent of design speed 



0732 




REAOING 


NUMBER 




0735 


0.981 




IGV TOTAL PRESSURE RATIO 


0.985 


t .20? 




ROTOR TOTAL PRESSURE RATIO 


1.163 


0.963 




STATOR 


TOTAL PRESSURE RATIO 


0.973 


0.999 




IGV TOTAL TEHPERATURE RATIO 


0.999 


1.062 




ROTOR TOTAL TEHPERATURE RATIO 


1.049 


0.999 




STATOR 


TOTAL TEHPERATURE RATIO 


0.999 


0.900 




ROTOR ADIABATIC EFFICIENCY 


0.903 


0.971 




ROTOR R0HEIITUH-R1 


ISE EFFICIENCY 


0.972 


0.253 




ROTOR HEAD-RISE COEFFICIENT 


0.250 


0.269 




FLOH COEFFICIENT 


0.269 


76.29 




AIRFLOH 


PER UHIT 


FRONTAL AREA 


68.16 


83.35 




AIRFLOH 


PER UNIT 


ANNULUS AREA 


74.46 


15.46 




AIRFLOH 


AT ORIFICE 


13.81 


15.44 




AIRFLOH 


AT IGV INLET 


13.79 


IMS 




AIRFLOH 


AT ROTOR 


INLET 


13.37 


14.78 
15.28 




AIRFLOH 


AT ROTOR 


OUTLET 


13.12 




AIRFLOH 


AT STATOR OUTLET 


13.62 


9788.4 




ROTATIVE SPEED 




8711.0 


89.9 




PERCENT 


OF DESIGN SPEED 


80.0 






COMPRESSOR PERFORMANCE 




1.142 




STAGE TOTAL PRESSURE RATIO 


1.114 


1.060 




STAGE TOTAL TEHPERATURE RATIO 


1.048 


0.646 




STAGE ADIABATIC EFFICIENCY 


0.658 


(f) 70 Percent of design speed 








0737 


0742 


0741 


0740 


073? 





.988 


0.985 


0.983 


0.981 


0.?7? 


1 


.120 


1.101 


1.083 


1.06? 


1.056 





.982 


0.990 


0.992 


0.990 


0.990 


1 


.000 


1.000 


0.999 


0.99? 


0.999 


1 


.036 


1.031 


1.027 


1.024 


1.021 


1 


.000 


0.99? 


0.998 


0.??7 


0.997 





.911 


0.895 


0.851 


0.808 


0.738 





.983 


1.021 


1.035 


1.017 


0.?72 


0, 


.241 


0.203 


0.166 


0.13? 


0.113 





.275 


0.302 


0.325 


0.342 


0.354 


61 


1.00 


66.72 


71.76 


75.47 


78.12 


66.65 


72.89 


78.40 


82.46 


85.35 


12.36 


13.52 


14.54 


15.30 


15.83 


12.37 


13.53 


14.57 


15.32 


15.85 


11 


.98 


13.14 


14.15 


14.86 


15.34 


1 J 


.74 


12.97 


14.09 


14.96 


15.37 


12 


(.20 


13.46 


14.40 


14.96 


15.35 


7605.7 


7613.5 


7637.6 


7633.8 


7640.6 


69.9 


69.9 


70.2 


70.1 


7C.2 


j 


086 


1.074 


1.057 


1.038 


1.024 


1 


036 


1.030 


1.025 


1.020 


1.017 


1. 


66? 


0.680 


0.644 


0.535 


0.38? 



(g) 60 Percent of design speed 

READING NUMBER 0743 

IGV TOTAL PRESSURE RATIO 0.991 

ROTOR TOTAL PRESSURE RATIO 1.085 

STATOR TOTAL PRESSURE RATIO 988 

IGV TOTAL TEHPERATURE RATIO x 000 

ROTOR TOTAL TEHPERATURE RATIO 1.026 

STATOR TOTAL TEHPERATURE RATIO i 000 

ROTOR ADIABATIC EFFICIENCY '.915 

ROTOR HOHEIITUM-RISE EFFICIENCY 991 

ROTOR HEAD-RISE COEFFICIENT 233 

FLOH COEFFICIENT 0.281 

AIRFLOH PER UHIT FRONTAL AREA 53.34 

AIRFLOH PER UNIT ANNULUS AREA 58 . 2 8 

AIRFLOH AT ORIFICE to .81 

AIRFLOU AT IGV INLET 10. 84 

AIRFLOH AT ROTOR INLET 10. 46 

AIRFLOH AT ROTOR OUTLET 10.35 

AIRFLOH AT STATOR OUTLET 10. 74 

ROTATIVE SPEED 6512.7 

PERCENT OF DESIGN SPEED 59.8 

COMPRESSOR PERFQRHANCE 

STAGE TOTAL PRESSURE RATIO 1 62 

STAGE TOTAL TEHPERATURE RATIO t " 026 

STAGE ADIABATIC EFFICIENCY 0682 



33 



Instrument 
survey planes: 
32 1— 



V Design 



Rotation 

2 



1 , , , 1 1 , , ! 




-32 -24 -16 



8 16 24 32 

Axial distance from rotor hub leading edge, cm 

Figure 1. - Flow path for stage 57M2. 




Figure 2. - Test stage. 



12 -10 

Axial distance, cm 



Figure 3. - Schematic of variable-inlet-guide vane. 



34 



Altitude 
exhaust 



Inlet control valves 
—1 22-m butterfly 7 




I 
\ 



0. 41 -m butterfly 



^-Straightening screen 



Collector throttle valve 7 
/ 
Col lector 7 / 
/ / 
1 Test stage / /^ speed 

\ ^Plenum \ / / increasing 

\ /chamber \J// gearbox 

\ n / • 




-d<[ 




EE-I7 ' 



Variable-speed 
drive motor 



l^-Atmosphere exhaust 

Figure 4. - Single-stage compressor test facility. 



133 



Atmosphere 



■Straightening screen 



35 




m 



3 



I 



up 



(a) Combination prooe. (b) Wedge static probe. 



II 



(c) Station 1 rake. (d) Station 3 rake. 

Figure 5. - Instrumentation 



36 




fouapijja Doeqeipv 



o|jej ajnssajd 



c o 1° — 
.2 — Z. <-> 
to -S c Sg 

E -g |j = 




37 




16 20 24 28 

Airflow, kg/sec 



Figure 8. - Overall performance of stage 
57M2A (IGV angle, 0°). 



38 



IGV angle, 




(a) 100 Percent of design speed. (b) 120 Percent of design speed. 

Figure 9. - Effect of inlet -guide-vane angle on overall stage performance. 



39 



O Maximum 
D Operating line 

(constant throttle valve position) 




30 20 10 -10 

Inlet guide vane setting angle, deg 

(b) 120 Percent of design speed. 

Figure 10. - Effect of inlet guide vane angle on calculated static thrust. 



40 



Report No 

NASA TP -1510 



Accession No. 



3. Recipient's Catalog No 



Title and Subtitle 

AERODYNAMIC PERFORMANCE OF AXIAL-FLOW FAN STAGE 
OPERATED AT NINE INLET GUIDE VANE ANGLES 



5. Report Date 

September 1979 



6. Performing Organization Code 



7. Author(s) 

Royce D. Moore and Lonnie Reid 



Performing Organization Report No 

E-9714 



9. Performing Organization Name and Address 

National Aeronautics and Space Administration 
Lewis Research Center 
Cleveland, Ohio 44135 



10. Work Unit No. 

505-04 



II. Contract or Grant No. 



12. Sponsoring Agency Name and Address 

National Aeronautics and Space Administration 
Washington, D.C. 20546 



13. Type of Report and Period Covered 

Technical Paper 



14. Sponsoring Agency Code 



15. Supplementary Notes 



Abstract 

The overall performance of a fan stage with nine inlet -guide -vane angle settings is presented. 
These data were obtained over the stable flow range at speeds from 60 to 120 percent of design 
for vane setting angles from -25° to 42. 5°. At design speed and design inlet guide vane angle, 
the stage had a peak efficiency of 0. 892 at a pressure ratio of 1. 322 and a flow of 25. 31 kilo- 
grams per second. The stall margin based on peak efficiency and stall was 20 percent. Based 
on an operating line passing through the peak efficiency point at the design setting angle, the use- 
ful operating range of the stage at design speed is limited by stall at the positive setting angles 
and by choke at the negative angles. At design speed the calculated static thrust along the oper- 
ating line varied from 68 to 114 percent of that obtained at design setting angle. 



17. Key Words (Suggested by Author(s)) 

Turbomachinery 

Compressor 

VTOL 

STOL 



18. Distribution Statement 

Unclassified - unlimited 
STAR Category 07 



19. Security Classif. (of this report) 

Unclassified 



20. Security Classif. (of this page) 

Unclassified 



21. No. of Pages 

42 



22. Price 

A03 



For sale by the National Technical Information Service, Springfield. Virginia 22161 



NASA-Langley, 1979 



National Aeronautics and 
Space Administration 

Washington, D.C. 
20546 

Official Business 

Penalty for Private Use, $300 



THIRD-CLASS BULK RATE 



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Postage and Fees Paid 
National Aeronautics and 
Space Administration 
NASA-451 



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